RG 14 10% AIRFOIL (rg1410-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: RG 14 10% AIRFOIL (rg1410-il) Reynolds number: 1,000,000 Max Cl/Cd: 89.44 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rg1410-il-1000000.txt Download as CSV file: xf-rg1410-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: RG 14 10% AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.9183 0.05545 0.05316 -0.0505 1.0000 0.0082
-13.500 -0.9504 0.04468 0.04215 -0.0604 1.0000 0.0081
-13.250 -0.9622 0.04022 0.03754 -0.0631 1.0000 0.0082
-13.000 -0.9790 0.03638 0.03350 -0.0634 1.0000 0.0082
-12.750 -0.9894 0.03390 0.03088 -0.0619 1.0000 0.0083
-12.500 -1.0020 0.03187 0.02869 -0.0584 1.0000 0.0083
-12.250 -1.0041 0.03076 0.02746 -0.0548 1.0000 0.0084
-12.000 -1.0010 0.02941 0.02597 -0.0522 1.0000 0.0085
-11.750 -1.0177 0.02600 0.02222 -0.0475 1.0000 0.0088
-11.500 -1.0130 0.02439 0.02044 -0.0447 1.0000 0.0089
-11.250 -1.0012 0.02343 0.01940 -0.0426 1.0000 0.0092
-11.000 -0.9870 0.02265 0.01855 -0.0407 1.0000 0.0094
-10.750 -0.9709 0.02205 0.01790 -0.0390 1.0000 0.0096
-10.500 -0.9542 0.02149 0.01728 -0.0374 1.0000 0.0099
-10.250 -0.9385 0.02077 0.01646 -0.0356 1.0000 0.0102
-10.000 -0.9221 0.02008 0.01568 -0.0338 1.0000 0.0106
-9.750 -0.9053 0.01945 0.01495 -0.0321 1.0000 0.0109
-9.500 -0.8864 0.01910 0.01453 -0.0306 1.0000 0.0112
-9.250 -0.8675 0.01878 0.01414 -0.0291 1.0000 0.0114
-9.000 -0.8591 0.01677 0.01193 -0.0263 1.0000 0.0121
-8.750 -0.8326 0.01617 0.01129 -0.0265 0.9992 0.0126
-8.500 -0.8002 0.01573 0.01080 -0.0278 0.9978 0.0131
-8.250 -0.7677 0.01520 0.01022 -0.0291 0.9963 0.0138
-8.000 -0.7344 0.01474 0.00969 -0.0305 0.9950 0.0145
-7.750 -0.7004 0.01441 0.00929 -0.0320 0.9938 0.0150
-7.500 -0.6727 0.01319 0.00796 -0.0325 0.9912 0.0159
-7.250 -0.6405 0.01270 0.00745 -0.0337 0.9889 0.0169
-7.000 -0.6070 0.01230 0.00703 -0.0351 0.9870 0.0177
-6.750 -0.5730 0.01185 0.00653 -0.0366 0.9855 0.0186
-6.500 -0.5382 0.01148 0.00612 -0.0382 0.9842 0.0193
-6.250 -0.5071 0.01086 0.00544 -0.0390 0.9820 0.0204
-6.000 -0.4782 0.01034 0.00489 -0.0394 0.9780 0.0219
-5.750 -0.4452 0.00998 0.00451 -0.0406 0.9755 0.0230
-5.500 -0.4107 0.00965 0.00415 -0.0420 0.9736 0.0243
-5.250 -0.3752 0.00935 0.00382 -0.0437 0.9721 0.0256
-5.000 -0.3426 0.00889 0.00336 -0.0447 0.9692 0.0289
-4.750 -0.3141 0.00861 0.00307 -0.0448 0.9631 0.0316
-4.500 -0.2818 0.00824 0.00274 -0.0457 0.9589 0.0400
-4.250 -0.2524 0.00789 0.00248 -0.0461 0.9525 0.0590
-4.000 -0.2220 0.00762 0.00227 -0.0466 0.9455 0.0763
-3.750 -0.1925 0.00735 0.00207 -0.0469 0.9372 0.0961
-3.500 -0.1626 0.00711 0.00189 -0.0473 0.9283 0.1192
-3.250 -0.1354 0.00689 0.00174 -0.0471 0.9165 0.1469
-3.000 -0.1087 0.00663 0.00160 -0.0469 0.9039 0.1839
-2.750 -0.0824 0.00640 0.00147 -0.0465 0.8907 0.2260
-2.500 -0.0566 0.00616 0.00136 -0.0461 0.8769 0.2773
-2.250 -0.0315 0.00586 0.00126 -0.0456 0.8628 0.3472
-2.000 -0.0065 0.00558 0.00117 -0.0450 0.8484 0.4206
-1.750 0.0186 0.00534 0.00110 -0.0445 0.8331 0.4880
-1.500 0.0432 0.00509 0.00103 -0.0438 0.8175 0.5641
-1.250 0.0678 0.00486 0.00098 -0.0430 0.8007 0.6351
-1.000 0.0913 0.00465 0.00098 -0.0420 0.7820 0.7199
-0.750 0.1159 0.00460 0.00101 -0.0411 0.7619 0.7752
-0.500 0.1416 0.00464 0.00103 -0.0404 0.7407 0.8025
-0.250 0.1676 0.00470 0.00104 -0.0398 0.7207 0.8210
0.000 0.1939 0.00476 0.00106 -0.0393 0.7022 0.8351
0.250 0.2202 0.00483 0.00108 -0.0388 0.6828 0.8468
0.500 0.2462 0.00491 0.00111 -0.0382 0.6616 0.8577
0.750 0.2723 0.00501 0.00114 -0.0377 0.6393 0.8686
1.000 0.2980 0.00510 0.00118 -0.0371 0.6170 0.8781
1.250 0.3241 0.00520 0.00122 -0.0366 0.5977 0.8863
1.500 0.3501 0.00530 0.00127 -0.0360 0.5769 0.8948
1.750 0.3754 0.00542 0.00132 -0.0354 0.5540 0.9031
2.000 0.4011 0.00554 0.00138 -0.0348 0.5315 0.9120
2.250 0.4260 0.00566 0.00144 -0.0340 0.5069 0.9196
2.500 0.4509 0.00583 0.00151 -0.0334 0.4778 0.9277
2.750 0.4750 0.00599 0.00160 -0.0325 0.4505 0.9359
3.000 0.4993 0.00614 0.00168 -0.0316 0.4249 0.9453
3.250 0.5233 0.00631 0.00178 -0.0307 0.4009 0.9554
3.500 0.5494 0.00649 0.00189 -0.0302 0.3761 0.9642
3.750 0.5771 0.00672 0.00201 -0.0302 0.3463 0.9731
4.000 0.6084 0.00696 0.00215 -0.0311 0.3181 0.9795
4.250 0.6398 0.00724 0.00230 -0.0320 0.2871 0.9845
4.500 0.6730 0.00757 0.00248 -0.0334 0.2503 0.9873
4.750 0.7053 0.00795 0.00269 -0.0347 0.2119 0.9904
5.000 0.7364 0.00837 0.00293 -0.0357 0.1737 0.9941
5.250 0.7698 0.00870 0.00316 -0.0372 0.1530 0.9968
5.500 0.8032 0.00898 0.00338 -0.0386 0.1389 0.9995
5.750 0.8232 0.00921 0.00357 -0.0372 0.1276 1.0000
6.000 0.8430 0.00945 0.00376 -0.0357 0.1159 1.0000
6.250 0.8644 0.00972 0.00398 -0.0345 0.1026 1.0000
6.500 0.8865 0.01004 0.00422 -0.0335 0.0893 1.0000
6.750 0.9095 0.01033 0.00448 -0.0326 0.0801 1.0000
7.000 0.9331 0.01062 0.00476 -0.0319 0.0723 1.0000
7.250 0.9560 0.01099 0.00507 -0.0311 0.0632 1.0000
7.500 0.9798 0.01127 0.00535 -0.0304 0.0574 1.0000
7.750 1.0032 0.01162 0.00567 -0.0297 0.0511 1.0000
8.000 1.0267 0.01195 0.00600 -0.0290 0.0459 1.0000
8.250 1.0498 0.01231 0.00636 -0.0283 0.0408 1.0000
8.500 1.0729 0.01268 0.00671 -0.0276 0.0367 1.0000
8.750 1.0954 0.01310 0.00712 -0.0268 0.0326 1.0000
9.000 1.1184 0.01345 0.00749 -0.0261 0.0297 1.0000
9.250 1.1396 0.01397 0.00800 -0.0251 0.0258 1.0000
9.500 1.1626 0.01430 0.00837 -0.0244 0.0239 1.0000
9.750 1.1834 0.01482 0.00887 -0.0234 0.0210 1.0000
10.000 1.2047 0.01527 0.00937 -0.0224 0.0190 1.0000
10.250 1.2251 0.01579 0.00988 -0.0214 0.0167 1.0000
10.500 1.2443 0.01640 0.01054 -0.0201 0.0147 1.0000
10.750 1.2641 0.01691 0.01109 -0.0190 0.0134 1.0000
11.000 1.2796 0.01775 0.01196 -0.0172 0.0117 1.0000
11.250 1.2985 0.01826 0.01253 -0.0160 0.0110 1.0000
11.500 1.3163 0.01882 0.01314 -0.0146 0.0103 1.0000
11.750 1.3315 0.01948 0.01384 -0.0128 0.0096 1.0000
12.000 1.3407 0.02035 0.01478 -0.0101 0.0090 1.0000
12.250 1.3485 0.02126 0.01579 -0.0072 0.0085 1.0000
12.500 1.3601 0.02197 0.01657 -0.0050 0.0083 1.0000
12.750 1.3701 0.02278 0.01746 -0.0027 0.0080 1.0000
13.000 1.3785 0.02370 0.01847 -0.0004 0.0078 1.0000
13.250 1.3859 0.02471 0.01956 0.0018 0.0075 1.0000
13.500 1.3930 0.02578 0.02070 0.0039 0.0072 1.0000
13.750 1.3967 0.02713 0.02214 0.0061 0.0070 1.0000
14.000 1.3990 0.02866 0.02376 0.0081 0.0068 1.0000
14.250 1.3918 0.03102 0.02625 0.0103 0.0065 1.0000
14.500 1.3910 0.03308 0.02842 0.0116 0.0065 1.0000
14.750 1.3795 0.03629 0.03178 0.0128 0.0063 1.0000
15.000 1.3729 0.03937 0.03500 0.0132 0.0062 1.0000
15.250 1.3709 0.04219 0.03794 0.0132 0.0062 1.0000
15.500 1.3640 0.04581 0.04169 0.0126 0.0062 1.0000
15.750 1.3616 0.04909 0.04509 0.0117 0.0061 1.0000
16.000 1.3465 0.05432 0.05046 0.0098 0.0061 1.0000
16.250 1.3374 0.05903 0.05530 0.0079 0.0060 1.0000
16.500 1.3251 0.06449 0.06090 0.0053 0.0060 1.0000
16.750 1.3153 0.06981 0.06634 0.0026 0.0059 1.0000
17.000 1.2929 0.07748 0.07416 -0.0014 0.0060 1.0000
17.250 1.2760 0.08455 0.08137 -0.0053 0.0059 1.0000
17.500 1.2541 0.09277 0.08973 -0.0098 0.0059 1.0000
17.750 1.2327 0.10118 0.09827 -0.0145 0.0060 1.0000
18.000 1.2106 0.10998 0.10720 -0.0195 0.0060 1.0000
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