RAF 38 AIRFOIL (raf38-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAF 38 AIRFOIL (raf38-il) Reynolds number: 500,000 Max Cl/Cd: 96.63 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-raf38-il-500000.txt Download as CSV file: xf-raf38-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: RAF 38 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.8549 0.06807 0.06508 -0.0556 1.0000 0.0205
-14.500 -0.8997 0.05602 0.05276 -0.0649 1.0000 0.0202
-14.250 -0.9243 0.04859 0.04511 -0.0707 1.0000 0.0203
-14.000 -0.9418 0.04332 0.03963 -0.0740 1.0000 0.0204
-13.750 -0.9551 0.03943 0.03555 -0.0753 1.0000 0.0205
-13.500 -0.9639 0.03661 0.03255 -0.0750 1.0000 0.0207
-13.250 -0.9722 0.03421 0.02997 -0.0736 1.0000 0.0209
-13.000 -0.9782 0.03231 0.02789 -0.0711 1.0000 0.0211
-12.750 -0.9804 0.03107 0.02647 -0.0680 1.0000 0.0214
-12.500 -0.9908 0.02918 0.02442 -0.0635 1.0000 0.0217
-12.250 -0.9902 0.02771 0.02287 -0.0602 1.0000 0.0221
-12.000 -0.9815 0.02686 0.02198 -0.0578 1.0000 0.0226
-11.750 -0.9716 0.02600 0.02106 -0.0554 1.0000 0.0230
-11.500 -0.9589 0.02544 0.02044 -0.0533 1.0000 0.0238
-11.250 -0.9476 0.02464 0.01953 -0.0509 1.0000 0.0244
-11.000 -0.9358 0.02384 0.01860 -0.0485 1.0000 0.0251
-10.750 -0.9243 0.02300 0.01760 -0.0460 1.0000 0.0257
-10.500 -0.9153 0.02185 0.01642 -0.0432 1.0000 0.0266
-10.250 -0.9019 0.02139 0.01594 -0.0409 1.0000 0.0272
-10.000 -0.8891 0.02098 0.01550 -0.0384 1.0000 0.0280
-9.750 -0.8611 0.02033 0.01476 -0.0390 0.9980 0.0292
-9.500 -0.8245 0.01969 0.01396 -0.0413 0.9944 0.0305
-9.250 -0.7917 0.01873 0.01300 -0.0430 0.9896 0.0321
-9.000 -0.7544 0.01847 0.01272 -0.0453 0.9851 0.0338
-8.750 -0.7188 0.01800 0.01214 -0.0471 0.9798 0.0356
-8.500 -0.6857 0.01707 0.01116 -0.0486 0.9732 0.0374
-8.250 -0.6495 0.01676 0.01085 -0.0506 0.9670 0.0392
-8.000 -0.6130 0.01646 0.01048 -0.0526 0.9589 0.0415
-7.750 -0.5777 0.01572 0.00964 -0.0544 0.9490 0.0437
-7.500 -0.5411 0.01515 0.00908 -0.0565 0.9376 0.0459
-7.250 -0.5060 0.01485 0.00871 -0.0581 0.9224 0.0485
-7.000 -0.4747 0.01466 0.00839 -0.0587 0.9045 0.0504
-6.750 -0.4503 0.01378 0.00743 -0.0582 0.8865 0.0529
-6.500 -0.4252 0.01347 0.00706 -0.0577 0.8706 0.0551
-6.250 -0.4003 0.01324 0.00673 -0.0571 0.8567 0.0574
-6.000 -0.3753 0.01303 0.00641 -0.0565 0.8445 0.0593
-5.750 -0.3511 0.01271 0.00601 -0.0557 0.8332 0.0610
-5.500 -0.3292 0.01214 0.00539 -0.0546 0.8226 0.0639
-5.250 -0.3051 0.01188 0.00506 -0.0538 0.8118 0.0662
-5.000 -0.2806 0.01164 0.00477 -0.0530 0.8009 0.0686
-4.750 -0.2556 0.01146 0.00450 -0.0524 0.7916 0.0705
-4.500 -0.2313 0.01116 0.00414 -0.0516 0.7829 0.0728
-4.250 -0.2071 0.01084 0.00379 -0.0508 0.7758 0.0762
-4.000 -0.1819 0.01061 0.00354 -0.0502 0.7681 0.0795
-3.500 -0.1309 0.01020 0.00307 -0.0491 0.7545 0.0891
-3.250 -0.1057 0.00997 0.00286 -0.0485 0.7478 0.1004
-3.000 -0.0827 0.00949 0.00268 -0.0477 0.7414 0.1697
-2.750 -0.0583 0.00917 0.00255 -0.0471 0.7348 0.2217
-2.500 -0.0335 0.00892 0.00242 -0.0465 0.7292 0.2665
-2.250 -0.0099 0.00856 0.00232 -0.0457 0.7228 0.3348
-2.000 0.0137 0.00825 0.00224 -0.0449 0.7165 0.4105
-1.750 0.0376 0.00801 0.00219 -0.0441 0.7107 0.4767
-1.500 0.0609 0.00774 0.00215 -0.0431 0.7043 0.5398
-1.250 0.0839 0.00750 0.00211 -0.0420 0.6986 0.6053
-1.000 0.1071 0.00731 0.00212 -0.0408 0.6929 0.6656
-0.750 0.1304 0.00713 0.00213 -0.0397 0.6864 0.7253
-0.500 0.1546 0.00704 0.00213 -0.0386 0.6805 0.7752
-0.250 0.1802 0.00693 0.00216 -0.0378 0.6740 0.8128
0.000 0.2075 0.00687 0.00220 -0.0374 0.6677 0.8528
0.250 0.2391 0.00689 0.00228 -0.0378 0.6617 0.8916
0.500 0.2760 0.00693 0.00236 -0.0394 0.6545 0.9164
1.000 0.3525 0.00716 0.00254 -0.0433 0.6399 0.9489
1.250 0.3897 0.00730 0.00261 -0.0451 0.6324 0.9578
1.500 0.4300 0.00739 0.00269 -0.0476 0.6221 0.9639
1.750 0.4670 0.00751 0.00276 -0.0494 0.6112 0.9713
2.000 0.5091 0.00763 0.00280 -0.0523 0.5994 0.9761
2.250 0.5466 0.00772 0.00288 -0.0543 0.5879 0.9829
2.500 0.5875 0.00778 0.00290 -0.0571 0.5748 0.9862
2.750 0.6254 0.00785 0.00292 -0.0593 0.5592 0.9905
3.000 0.6628 0.00793 0.00296 -0.0614 0.5444 0.9945
3.250 0.7017 0.00798 0.00296 -0.0639 0.5300 0.9981
3.500 0.7334 0.00805 0.00299 -0.0649 0.5142 1.0000
3.750 0.7541 0.00814 0.00304 -0.0635 0.5001 1.0000
4.000 0.7747 0.00826 0.00310 -0.0621 0.4852 1.0000
4.250 0.7954 0.00840 0.00319 -0.0608 0.4712 1.0000
4.500 0.8161 0.00855 0.00330 -0.0594 0.4567 1.0000
5.000 0.8579 0.00889 0.00357 -0.0567 0.4299 1.0000
5.250 0.8784 0.00909 0.00373 -0.0553 0.4144 1.0000
5.500 0.8986 0.00930 0.00390 -0.0538 0.3978 1.0000
5.750 0.9186 0.00953 0.00409 -0.0523 0.3805 1.0000
6.000 0.9386 0.00977 0.00428 -0.0508 0.3600 1.0000
6.250 0.9569 0.01009 0.00451 -0.0490 0.3326 1.0000
6.500 0.9731 0.01054 0.00479 -0.0469 0.2936 1.0000
6.750 0.9862 0.01116 0.00518 -0.0444 0.2502 1.0000
7.250 1.0102 0.01256 0.00614 -0.0389 0.1694 1.0000
8.000 1.0412 0.01485 0.00788 -0.0301 0.0806 1.0000
8.250 1.0541 0.01542 0.00842 -0.0275 0.0744 1.0000
8.500 1.0694 0.01584 0.00889 -0.0254 0.0706 1.0000
8.750 1.0809 0.01642 0.00946 -0.0227 0.0666 1.0000
9.000 1.0882 0.01700 0.01007 -0.0192 0.0633 1.0000
9.250 1.1006 0.01742 0.01054 -0.0166 0.0607 1.0000
9.500 1.1111 0.01797 0.01111 -0.0139 0.0576 1.0000
9.750 1.1151 0.01888 0.01203 -0.0104 0.0542 1.0000
10.000 1.1293 0.01938 0.01259 -0.0086 0.0520 1.0000
10.250 1.1423 0.01998 0.01323 -0.0067 0.0491 1.0000
10.500 1.1502 0.02091 0.01416 -0.0044 0.0464 1.0000
10.750 1.1590 0.02186 0.01517 -0.0023 0.0441 1.0000
11.000 1.1729 0.02255 0.01591 -0.0010 0.0415 1.0000
11.250 1.1836 0.02349 0.01686 0.0005 0.0394 1.0000
11.500 1.1879 0.02494 0.01834 0.0024 0.0374 1.0000
11.750 1.2003 0.02588 0.01936 0.0035 0.0357 1.0000
12.000 1.2113 0.02697 0.02050 0.0046 0.0341 1.0000
12.250 1.2187 0.02838 0.02192 0.0057 0.0326 1.0000
12.500 1.2213 0.03023 0.02383 0.0071 0.0312 1.0000
12.750 1.2315 0.03152 0.02520 0.0079 0.0300 1.0000
13.000 1.2402 0.03297 0.02671 0.0086 0.0288 1.0000
13.250 1.2467 0.03464 0.02842 0.0093 0.0277 1.0000
13.500 1.2484 0.03679 0.03061 0.0101 0.0270 1.0000
13.750 1.2477 0.03919 0.03309 0.0109 0.0260 1.0000
14.000 1.2531 0.04111 0.03511 0.0115 0.0254 1.0000
14.250 1.2577 0.04313 0.03722 0.0119 0.0246 1.0000
14.500 1.2619 0.04524 0.03940 0.0121 0.0239 1.0000
14.750 1.2652 0.04749 0.04171 0.0123 0.0233 1.0000
15.000 1.2670 0.04996 0.04422 0.0124 0.0227 1.0000
15.250 1.2626 0.05306 0.04736 0.0126 0.0220 1.0000
15.500 1.2617 0.05586 0.05024 0.0127 0.0217 1.0000
15.750 1.2642 0.05847 0.05298 0.0125 0.0213 1.0000
16.000 1.2659 0.06123 0.05585 0.0122 0.0209 1.0000
16.250 1.2661 0.06421 0.05893 0.0118 0.0203 1.0000
16.500 1.2663 0.06723 0.06204 0.0112 0.0200 1.0000
16.750 1.2658 0.07039 0.06528 0.0106 0.0196 1.0000
17.000 1.2652 0.07364 0.06861 0.0098 0.0192 1.0000
17.250 1.2641 0.07700 0.07203 0.0090 0.0189 1.0000
17.500 1.2611 0.08053 0.07561 0.0081 0.0185 1.0000
17.750 1.2572 0.08409 0.07923 0.0075 0.0182 1.0000
18.000 1.2517 0.08812 0.08338 0.0065 0.0178 1.0000
18.250 1.2481 0.09205 0.08745 0.0052 0.0177 1.0000
18.500 1.2424 0.09651 0.09204 0.0034 0.0174 1.0000
18.750 1.2369 0.10091 0.09657 0.0017 0.0172 1.0000
19.000 1.2307 0.10555 0.10133 -0.0003 0.0170 1.0000
19.250 1.2226 0.11048 0.10640 -0.0024 0.0168 1.0000
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Polar data table (+)
Polar graphs
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