RAF 89 AIRFOIL (raf89-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAF 89 AIRFOIL (raf89-il) Reynolds number: 200,000 Max Cl/Cd: 35.96 at α=9.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-raf89-il-200000-n5.txt Download as CSV file: xf-raf89-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RAF 89 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.250 -0.8370 0.09721 0.09082 -0.0724 1.0000 0.0914
-19.000 -0.8382 0.09413 0.08769 -0.0734 1.0000 0.0929
-18.750 -0.8403 0.09093 0.08441 -0.0745 1.0000 0.0946
-18.500 -0.8397 0.08819 0.08166 -0.0752 1.0000 0.0961
-18.250 -0.8389 0.08555 0.07904 -0.0759 1.0000 0.0977
-18.000 -0.8408 0.08255 0.07602 -0.0768 1.0000 0.0996
-17.750 -0.8430 0.07954 0.07296 -0.0775 1.0000 0.1016
-17.500 -0.8459 0.07643 0.06976 -0.0783 1.0000 0.1039
-17.250 -0.8475 0.07367 0.06702 -0.0788 1.0000 0.1059
-17.000 -0.8514 0.07064 0.06399 -0.0793 1.0000 0.1082
-16.750 -0.8543 0.06779 0.06111 -0.0797 1.0000 0.1106
-16.500 -0.8558 0.06514 0.05839 -0.0800 1.0000 0.1131
-16.250 -0.8597 0.06237 0.05563 -0.0802 1.0000 0.1155
-16.000 -0.8645 0.05962 0.05287 -0.0802 1.0000 0.1182
-15.750 -0.8675 0.05715 0.05037 -0.0800 1.0000 0.1210
-15.500 -0.8693 0.05491 0.04808 -0.0796 1.0000 0.1240
-15.250 -0.8754 0.05246 0.04566 -0.0790 1.0000 0.1268
-14.750 -0.8589 0.04732 0.04047 -0.0818 0.9865 0.1350
-14.500 -0.8484 0.04470 0.03784 -0.0841 0.9746 0.1393
-14.250 -0.8343 0.04246 0.03556 -0.0863 0.9610 0.1445
-14.000 -0.8175 0.04031 0.03336 -0.0890 0.9476 0.1495
-13.750 -0.7970 0.03817 0.03118 -0.0923 0.9351 0.1551
-13.500 -0.7683 0.03629 0.02921 -0.0965 0.9240 0.1611
-13.250 -0.7393 0.03433 0.02721 -0.1011 0.9116 0.1674
-13.000 -0.7054 0.03269 0.02545 -0.1060 0.8993 0.1742
-12.750 -0.6755 0.03106 0.02377 -0.1102 0.8854 0.1807
-12.500 -0.6453 0.02982 0.02239 -0.1136 0.8724 0.1871
-12.250 -0.6200 0.02854 0.02106 -0.1164 0.8599 0.1927
-12.000 -0.5993 0.02754 0.01996 -0.1177 0.8477 0.1985
-11.750 -0.5798 0.02662 0.01895 -0.1186 0.8366 0.2037
-11.500 -0.5665 0.02578 0.01806 -0.1182 0.8264 0.2086
-11.250 -0.5520 0.02505 0.01723 -0.1177 0.8172 0.2140
-11.000 -0.5374 0.02436 0.01646 -0.1172 0.8098 0.2188
-10.750 -0.5284 0.02369 0.01579 -0.1156 0.8025 0.2238
-10.500 -0.5168 0.02310 0.01513 -0.1142 0.7955 0.2293
-10.250 -0.5045 0.02255 0.01451 -0.1129 0.7893 0.2343
-10.000 -0.4948 0.02201 0.01395 -0.1111 0.7834 0.2395
-9.750 -0.4848 0.02153 0.01343 -0.1091 0.7772 0.2453
-9.500 -0.4726 0.02110 0.01295 -0.1074 0.7718 0.2501
-9.250 -0.4620 0.02066 0.01250 -0.1054 0.7670 0.2552
-9.000 -0.4482 0.02029 0.01206 -0.1037 0.7627 0.2604
-8.750 -0.4359 0.01997 0.01168 -0.1017 0.7577 0.2653
-8.500 -0.4251 0.01960 0.01136 -0.0994 0.7526 0.2697
-8.250 -0.4134 0.01929 0.01103 -0.0972 0.7479 0.2747
-8.000 -0.3992 0.01902 0.01069 -0.0953 0.7438 0.2801
-7.750 -0.3834 0.01876 0.01037 -0.0935 0.7400 0.2849
-7.500 -0.3718 0.01848 0.01013 -0.0911 0.7357 0.2897
-7.250 -0.3595 0.01824 0.00990 -0.0887 0.7312 0.2949
-7.000 -0.3452 0.01804 0.00964 -0.0865 0.7267 0.3002
-6.750 -0.3312 0.01780 0.00940 -0.0843 0.7226 0.3052
-6.500 -0.3163 0.01758 0.00916 -0.0821 0.7185 0.3103
-6.250 -0.3004 0.01740 0.00894 -0.0801 0.7145 0.3157
-6.000 -0.2871 0.01728 0.00878 -0.0776 0.7094 0.3209
-5.750 -0.2748 0.01709 0.00865 -0.0748 0.7041 0.3258
-5.500 -0.2610 0.01695 0.00851 -0.0723 0.6993 0.3312
-5.250 -0.2445 0.01684 0.00834 -0.0702 0.6953 0.3370
-5.000 -0.2276 0.01675 0.00820 -0.0682 0.6913 0.3425
-4.750 -0.2156 0.01663 0.00815 -0.0653 0.6865 0.3480
-4.500 -0.2000 0.01652 0.00806 -0.0630 0.6819 0.3543
-4.250 -0.1817 0.01642 0.00792 -0.0612 0.6773 0.3606
-4.000 -0.1629 0.01626 0.00778 -0.0596 0.6734 0.3670
-3.750 -0.1426 0.01613 0.00763 -0.0582 0.6697 0.3742
-3.500 -0.1268 0.01606 0.00759 -0.0559 0.6647 0.3811
-3.250 -0.1099 0.01594 0.00752 -0.0538 0.6596 0.3878
-3.000 -0.0919 0.01581 0.00741 -0.0519 0.6550 0.3959
-2.500 -0.0518 0.01555 0.00717 -0.0489 0.6465 0.4132
-2.250 -0.0362 0.01547 0.00716 -0.0466 0.6409 0.4226
-2.000 -0.0193 0.01536 0.00711 -0.0444 0.6355 0.4323
-1.750 0.0001 0.01524 0.00701 -0.0427 0.6307 0.4448
-1.500 0.0201 0.01513 0.00694 -0.0411 0.6263 0.4578
-1.250 0.0343 0.01510 0.00701 -0.0384 0.6201 0.4710
-0.750 0.0716 0.01501 0.00700 -0.0346 0.6089 0.5014
-0.500 0.0906 0.01501 0.00703 -0.0328 0.6034 0.5154
-0.250 0.1071 0.01504 0.00709 -0.0305 0.5966 0.5281
0.000 0.1267 0.01503 0.00706 -0.0288 0.5903 0.5402
0.250 0.1475 0.01504 0.00703 -0.0272 0.5845 0.5501
0.500 0.1631 0.01508 0.00710 -0.0248 0.5771 0.5596
0.750 0.1822 0.01508 0.00706 -0.0230 0.5702 0.5678
1.000 0.2016 0.01509 0.00706 -0.0213 0.5636 0.5758
1.250 0.2162 0.01513 0.00708 -0.0186 0.5556 0.5838
1.500 0.2355 0.01513 0.00705 -0.0169 0.5484 0.5902
1.750 0.2507 0.01515 0.00710 -0.0144 0.5405 0.5966
2.000 0.2636 0.01518 0.00708 -0.0114 0.5324 0.6035
2.250 0.2787 0.01520 0.00704 -0.0089 0.5250 0.6095
2.500 0.2914 0.01523 0.00713 -0.0060 0.5166 0.6148
2.750 0.3069 0.01528 0.00714 -0.0036 0.5089 0.6206
3.000 0.3195 0.01540 0.00723 -0.0007 0.5006 0.6266
3.250 0.3335 0.01552 0.00731 0.0018 0.4924 0.6318
3.500 0.3491 0.01564 0.00744 0.0041 0.4848 0.6369
3.750 0.3627 0.01580 0.00761 0.0066 0.4766 0.6425
4.000 0.3782 0.01597 0.00771 0.0088 0.4693 0.6481
4.250 0.3915 0.01618 0.00791 0.0113 0.4618 0.6534
4.500 0.4063 0.01636 0.00811 0.0135 0.4544 0.6584
4.750 0.4222 0.01655 0.00828 0.0155 0.4478 0.6641
5.000 0.4354 0.01679 0.00855 0.0178 0.4407 0.6698
5.500 0.4662 0.01725 0.00899 0.0218 0.4281 0.6819
5.750 0.4789 0.01752 0.00932 0.0241 0.4216 0.6899
6.250 0.5089 0.01806 0.00985 0.0280 0.4097 0.7074
6.500 0.5217 0.01837 0.01025 0.0301 0.4039 0.7176
6.750 0.5354 0.01868 0.01062 0.0321 0.3980 0.7280
7.000 0.5503 0.01900 0.01094 0.0339 0.3927 0.7398
7.250 0.5658 0.01932 0.01132 0.0355 0.3873 0.7507
7.500 0.5797 0.01971 0.01177 0.0373 0.3816 0.7629
7.750 0.5967 0.02007 0.01219 0.0384 0.3763 0.7756
8.000 0.6154 0.02041 0.01252 0.0394 0.3712 0.7907
8.250 0.6343 0.02086 0.01310 0.0399 0.3659 0.8084
8.500 0.6610 0.02134 0.01370 0.0389 0.3600 0.8288
8.750 0.6992 0.02186 0.01428 0.0357 0.3542 0.8525
9.000 0.7482 0.02253 0.01507 0.0302 0.3480 0.8788
9.250 0.8028 0.02334 0.01600 0.0233 0.3409 0.9034
9.500 0.8550 0.02413 0.01678 0.0171 0.3348 0.9250
9.750 0.8972 0.02495 0.01768 0.0126 0.3290 0.9489
10.000 0.9271 0.02580 0.01857 0.0105 0.3231 0.9752
10.250 0.9536 0.02693 0.01964 0.0092 0.3178 0.9986
10.500 0.9689 0.02769 0.02038 0.0099 0.3134 1.0000
10.750 0.9760 0.02847 0.02119 0.0119 0.3086 1.0000
11.000 0.9840 0.02926 0.02197 0.0137 0.3040 1.0000
11.250 0.9931 0.03004 0.02270 0.0154 0.2997 1.0000
11.500 1.0026 0.03086 0.02352 0.0170 0.2956 1.0000
11.750 1.0107 0.03182 0.02453 0.0185 0.2909 1.0000
12.000 1.0191 0.03278 0.02549 0.0199 0.2861 1.0000
12.250 1.0283 0.03372 0.02637 0.0213 0.2818 1.0000
12.500 1.0368 0.03479 0.02747 0.0225 0.2773 1.0000
12.750 1.0440 0.03599 0.02871 0.0237 0.2723 1.0000
13.000 1.0504 0.03722 0.02992 0.0250 0.2669 1.0000
13.250 1.0572 0.03850 0.03118 0.0261 0.2616 1.0000
13.500 1.0616 0.04003 0.03277 0.0272 0.2556 1.0000
13.750 1.0681 0.04141 0.03413 0.0281 0.2505 1.0000
14.000 1.0736 0.04293 0.03566 0.0290 0.2454 1.0000
14.250 1.0797 0.04449 0.03727 0.0298 0.2404 1.0000
14.500 1.0856 0.04607 0.03886 0.0305 0.2359 1.0000
14.750 1.0927 0.04755 0.04031 0.0312 0.2320 1.0000
15.000 1.0972 0.04940 0.04224 0.0317 0.2272 1.0000
15.250 1.1015 0.05124 0.04412 0.0322 0.2225 1.0000
15.500 1.1070 0.05298 0.04583 0.0327 0.2184 1.0000
15.750 1.1105 0.05501 0.04792 0.0331 0.2139 1.0000
16.000 1.1134 0.05714 0.05012 0.0334 0.2092 1.0000
16.250 1.1160 0.05928 0.05225 0.0337 0.2048 1.0000
16.500 1.1194 0.06142 0.05443 0.0338 0.2007 1.0000
16.750 1.1197 0.06394 0.05702 0.0339 0.1959 1.0000
17.000 1.1206 0.06640 0.05949 0.0339 0.1914 1.0000
17.250 1.1218 0.06886 0.06198 0.0339 0.1872 1.0000
17.500 1.1197 0.07180 0.06500 0.0337 0.1823 1.0000
17.750 1.1192 0.07453 0.06775 0.0335 0.1777 1.0000
18.000 1.1167 0.07754 0.07079 0.0332 0.1731 1.0000
18.250 1.1128 0.08082 0.07416 0.0327 0.1681 1.0000
18.500 1.1107 0.08384 0.07717 0.0323 0.1636 1.0000
18.750 1.1065 0.08723 0.08063 0.0316 0.1590 1.0000
19.000 1.1014 0.09074 0.08420 0.0309 0.1541 1.0000
19.250 1.0984 0.09398 0.08740 0.0302 0.1497 1.0000
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