RAF 26 AIRFOIL (raf26-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAF 26 AIRFOIL (raf26-il) Reynolds number: 100,000 Max Cl/Cd: 53.82 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-raf26-il-100000.txt Download as CSV file: xf-raf26-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: RAF 26 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5022 0.10857 0.10343 -0.0165 1.0000 0.0790
-9.000 -0.5133 0.10651 0.10147 -0.0211 1.0000 0.0802
-8.750 -0.5257 0.10420 0.09928 -0.0251 1.0000 0.0805
-8.500 -0.4967 0.09755 0.09255 -0.0188 1.0000 0.0842
-8.250 -0.4929 0.09439 0.08943 -0.0188 1.0000 0.0876
-8.000 -0.4077 0.07977 0.07516 -0.0234 1.0000 0.1000
-7.750 -0.4120 0.07642 0.07186 -0.0240 1.0000 0.1041
-7.500 -0.4278 0.07340 0.06895 -0.0257 1.0000 0.1064
-7.250 -0.5034 0.08076 0.07609 -0.0248 1.0000 0.0980
-7.000 -0.4987 0.07742 0.07277 -0.0256 1.0000 0.1025
-6.750 -0.5050 0.07207 0.06726 -0.0380 1.0000 0.1084
-6.500 -0.4922 0.06909 0.06446 -0.0312 1.0000 0.1120
-6.250 -0.4891 0.06447 0.05959 -0.0387 1.0000 0.1224
-6.000 -0.4770 0.06214 0.05748 -0.0330 1.0000 0.1304
-5.750 -0.4686 0.05838 0.05366 -0.0340 1.0000 0.1407
-5.500 -0.4584 0.05468 0.04987 -0.0353 1.0000 0.1528
-5.250 -0.4461 0.05248 0.04724 -0.0381 1.0000 0.1767
-5.000 -0.4342 0.04834 0.04335 -0.0349 1.0000 0.1809
-4.750 -0.3959 0.03575 0.02892 -0.0410 1.0000 0.0797
-4.500 -0.3748 0.03088 0.02341 -0.0396 1.0000 0.0660
-4.250 -0.3548 0.02751 0.01964 -0.0385 1.0000 0.0634
-4.000 -0.3329 0.02499 0.01663 -0.0371 1.0000 0.0631
-3.750 -0.3101 0.02368 0.01472 -0.0354 1.0000 0.0672
-3.500 -0.2871 0.02109 0.01193 -0.0344 1.0000 0.0693
-3.250 -0.2639 0.01953 0.01025 -0.0332 1.0000 0.0738
-3.000 -0.2411 0.01826 0.00888 -0.0320 1.0000 0.0843
-2.750 -0.2186 0.01708 0.00772 -0.0307 1.0000 0.0981
-2.500 -0.1973 0.01598 0.00674 -0.0294 1.0000 0.1265
-2.250 -0.1769 0.01428 0.00580 -0.0281 1.0000 0.2423
-2.000 -0.1182 0.01157 0.00559 -0.0327 1.0000 1.0000
-1.750 -0.0974 0.01166 0.00534 -0.0317 1.0000 1.0000
-1.500 -0.0769 0.01178 0.00518 -0.0306 1.0000 1.0000
-1.250 -0.0565 0.01192 0.00506 -0.0296 1.0000 1.0000
-1.000 -0.0362 0.01209 0.00503 -0.0285 1.0000 1.0000
-0.750 -0.0161 0.01229 0.00506 -0.0275 1.0000 1.0000
-0.500 0.0038 0.01251 0.00513 -0.0266 1.0000 1.0000
-0.250 0.0236 0.01277 0.00526 -0.0256 1.0000 1.0000
0.000 0.0433 0.01305 0.00541 -0.0247 1.0000 1.0000
0.250 0.0627 0.01336 0.00564 -0.0239 1.0000 1.0000
0.500 0.0820 0.01371 0.00591 -0.0230 1.0000 1.0000
0.750 0.1012 0.01408 0.00623 -0.0223 1.0000 1.0000
1.000 0.1402 0.01461 0.00672 -0.0255 0.9935 1.0000
1.250 0.1851 0.01510 0.00721 -0.0297 0.9845 1.0000
1.500 0.2276 0.01548 0.00761 -0.0333 0.9745 1.0000
1.750 0.2721 0.01580 0.00797 -0.0372 0.9634 1.0000
2.000 0.3226 0.01593 0.00821 -0.0419 0.9496 1.0000
2.250 0.3780 0.01582 0.00824 -0.0471 0.9345 1.0000
2.500 0.4363 0.01548 0.00809 -0.0525 0.9194 1.0000
2.750 0.4941 0.01488 0.00775 -0.0573 0.9023 1.0000
3.000 0.5554 0.01403 0.00717 -0.0621 0.8798 1.0000
3.250 0.6015 0.01347 0.00688 -0.0640 0.8521 1.0000
3.500 0.6358 0.01309 0.00668 -0.0635 0.8136 1.0000
3.750 0.6643 0.01283 0.00651 -0.0618 0.7616 1.0000
4.000 0.6878 0.01278 0.00635 -0.0588 0.6736 1.0000
4.250 0.6921 0.01420 0.00630 -0.0524 0.3878 1.0000
4.500 0.6947 0.01687 0.00742 -0.0482 0.1732 1.0000
4.750 0.7106 0.01835 0.00862 -0.0459 0.1205 1.0000
5.000 0.7254 0.02038 0.01040 -0.0433 0.0876 1.0000
5.250 0.7479 0.02280 0.01270 -0.0419 0.0731 1.0000
5.500 0.7730 0.02488 0.01483 -0.0411 0.0623 1.0000
5.750 0.7999 0.02704 0.01713 -0.0403 0.0575 1.0000
6.000 0.8263 0.03038 0.02060 -0.0398 0.0549 1.0000
6.250 0.8490 0.03381 0.02442 -0.0384 0.0541 1.0000
6.500 0.8679 0.03550 0.02680 -0.0358 0.0515 1.0000
6.750 0.8852 0.03873 0.03053 -0.0337 0.0513 1.0000
7.000 0.9001 0.04306 0.03523 -0.0316 0.0530 1.0000
7.250 0.9108 0.04813 0.04121 -0.0278 0.0641 1.0000
9.000 0.9004 0.08618 0.08149 -0.0183 0.1182 1.0000
9.250 0.8614 0.08990 0.08530 -0.0192 0.1171 1.0000
9.500 0.8335 0.09619 0.09158 -0.0253 0.1157 1.0000
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Polar data table (+)
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