BOEING-VERTOL VR-5 AIRFOIL (vr5-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-5 AIRFOIL (vr5-il) Reynolds number: 100,000 Max Cl/Cd: 55.23 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-vr5-il-100000.txt Download as CSV file: xf-vr5-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: BOEING-VERTOL VR-5 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2906 0.09866 0.09459 -0.0326 1.0000 0.0911
-9.500 -0.3056 0.09552 0.09152 -0.0380 1.0000 0.0927
-9.250 -0.3218 0.09222 0.08829 -0.0434 1.0000 0.0932
-9.000 -0.2845 0.08702 0.08309 -0.0377 1.0000 0.0981
-8.750 -0.2923 0.08537 0.08153 -0.0364 1.0000 0.1003
-8.500 -0.2989 0.08287 0.07908 -0.0372 0.9961 0.1031
-8.250 -0.3089 0.07710 0.07333 -0.0476 0.9868 0.1073
-8.000 -0.4499 0.08665 0.08241 -0.0497 0.9903 0.0934
-7.750 -0.4089 0.08178 0.07789 -0.0388 0.9946 0.0997
-7.500 -0.3994 0.07590 0.07147 -0.0608 0.9758 0.1083
-7.250 -0.3667 0.06924 0.06510 -0.0601 0.9736 0.1123
-7.000 -0.3515 0.06629 0.06150 -0.0713 0.9593 0.1242
-6.750 -0.3249 0.06047 0.05606 -0.0702 0.9525 0.1286
-6.500 -0.3096 0.05695 0.05220 -0.0748 0.9402 0.1413
-6.250 -0.2907 0.05421 0.04919 -0.0771 0.9301 0.1559
-6.000 -0.2717 0.05087 0.04601 -0.0762 0.9199 0.1649
-5.750 -0.2600 0.04836 0.04330 -0.0768 0.9086 0.1882
-5.500 -0.2428 0.04593 0.04092 -0.0758 0.9005 0.2095
-5.250 -0.2300 0.04387 0.03884 -0.0746 0.8902 0.2395
-5.000 -0.2178 0.04244 0.03724 -0.0738 0.8803 0.2796
-4.750 -0.2006 0.03996 0.03489 -0.0716 0.8730 0.3051
-4.500 -0.1534 0.03508 0.02847 -0.0771 0.8634 0.1895
-4.250 -0.1072 0.03086 0.02254 -0.0749 0.8579 0.0920
-4.000 -0.0822 0.02898 0.02040 -0.0744 0.8495 0.0907
-3.750 -0.0555 0.02805 0.01904 -0.0734 0.8434 0.0932
-3.500 -0.0298 0.02651 0.01731 -0.0730 0.8355 0.0943
-3.250 -0.0041 0.02519 0.01598 -0.0724 0.8294 0.0987
-3.000 0.0219 0.02448 0.01519 -0.0720 0.8226 0.1036
-2.750 0.0484 0.02380 0.01439 -0.0714 0.8163 0.1071
-2.500 0.0731 0.02291 0.01359 -0.0703 0.8119 0.1144
-2.250 0.0977 0.02263 0.01332 -0.0702 0.8037 0.1228
-2.000 0.1214 0.02199 0.01276 -0.0692 0.7988 0.1341
-1.750 0.1452 0.02156 0.01240 -0.0688 0.7929 0.1603
-1.500 0.1458 0.01934 0.01277 -0.0627 0.7868 0.7780
-1.250 0.1525 0.01958 0.01312 -0.0546 0.7828 0.8927
-1.000 0.3028 0.01919 0.01223 -0.0727 0.7825 1.0000
-0.750 0.3240 0.01953 0.01248 -0.0732 0.7752 1.0000
-0.500 0.3429 0.01966 0.01249 -0.0724 0.7696 1.0000
-0.250 0.3614 0.01987 0.01261 -0.0717 0.7644 1.0000
0.000 0.3786 0.02031 0.01299 -0.0713 0.7572 1.0000
0.250 0.3962 0.02042 0.01299 -0.0699 0.7529 1.0000
0.500 0.4106 0.02107 0.01361 -0.0691 0.7459 1.0000
0.750 0.4268 0.02145 0.01391 -0.0679 0.7403 1.0000
1.000 0.4470 0.02154 0.01390 -0.0664 0.7368 1.0000
1.250 0.4614 0.02255 0.01489 -0.0661 0.7286 1.0000
1.500 0.4845 0.02286 0.01514 -0.0656 0.7241 1.0000
1.750 0.5110 0.02293 0.01512 -0.0649 0.7211 1.0000
2.000 0.5284 0.02419 0.01639 -0.0654 0.7120 1.0000
2.250 0.5550 0.02438 0.01655 -0.0650 0.7079 1.0000
2.500 0.5765 0.02522 0.01739 -0.0651 0.7009 1.0000
2.750 0.6024 0.02536 0.01750 -0.0646 0.6940 1.0000
3.000 0.6290 0.02533 0.01745 -0.0638 0.6872 1.0000
3.250 0.6541 0.02544 0.01757 -0.0631 0.6785 1.0000
3.500 0.6853 0.02487 0.01695 -0.0620 0.6749 1.0000
3.750 0.7038 0.02609 0.01826 -0.0623 0.6640 1.0000
4.000 0.7340 0.02579 0.01796 -0.0616 0.6603 1.0000
4.250 0.7528 0.02698 0.01926 -0.0617 0.6499 1.0000
4.500 0.7832 0.02663 0.01893 -0.0610 0.6457 1.0000
4.750 0.8029 0.02764 0.02004 -0.0609 0.6354 1.0000
5.000 0.8336 0.02724 0.01970 -0.0602 0.6307 1.0000
5.250 0.8532 0.02823 0.02082 -0.0600 0.6204 1.0000
5.500 0.8846 0.02774 0.02038 -0.0593 0.6156 1.0000
5.750 0.9052 0.02850 0.02127 -0.0589 0.6047 1.0000
6.000 0.9398 0.02743 0.02026 -0.0579 0.5997 1.0000
6.250 0.9627 0.02766 0.02063 -0.0571 0.5877 1.0000
6.500 0.9897 0.02721 0.02028 -0.0561 0.5765 1.0000
6.750 1.0229 0.02577 0.01890 -0.0546 0.5657 1.0000
7.000 1.0541 0.02441 0.01756 -0.0532 0.5518 1.0000
7.250 1.0812 0.02361 0.01685 -0.0519 0.5354 1.0000
7.500 1.1070 0.02298 0.01634 -0.0507 0.5170 1.0000
7.750 1.1330 0.02225 0.01569 -0.0494 0.4967 1.0000
8.000 1.1555 0.02188 0.01546 -0.0482 0.4723 1.0000
8.250 1.1765 0.02163 0.01536 -0.0468 0.4416 1.0000
8.500 1.1941 0.02162 0.01533 -0.0451 0.3974 1.0000
8.750 1.2013 0.02254 0.01586 -0.0425 0.3231 1.0000
9.000 1.1917 0.02499 0.01762 -0.0390 0.2380 1.0000
9.250 1.1760 0.02797 0.02003 -0.0357 0.1711 1.0000
9.500 1.1646 0.03102 0.02266 -0.0332 0.1386 1.0000
9.750 1.1577 0.03387 0.02524 -0.0311 0.1198 1.0000
10.000 1.1572 0.03633 0.02753 -0.0291 0.1048 1.0000
10.250 1.1615 0.03846 0.02958 -0.0275 0.0927 1.0000
10.500 1.1713 0.04028 0.03144 -0.0258 0.0833 1.0000
10.750 1.1866 0.04197 0.03307 -0.0241 0.0756 1.0000
11.000 1.2060 0.04359 0.03453 -0.0227 0.0686 1.0000
11.250 1.2333 0.04542 0.03652 -0.0214 0.0641 1.0000
11.500 1.2592 0.04746 0.03875 -0.0206 0.0608 1.0000
11.750 1.2890 0.04991 0.04120 -0.0203 0.0575 1.0000
12.000 1.3098 0.05348 0.04500 -0.0198 0.0552 1.0000
12.250 1.3109 0.05615 0.04804 -0.0182 0.0542 1.0000
12.500 1.3119 0.05938 0.05162 -0.0167 0.0537 1.0000
12.750 1.3083 0.06290 0.05547 -0.0154 0.0534 1.0000
13.000 1.3005 0.06669 0.05959 -0.0142 0.0533 1.0000
13.250 1.2891 0.07079 0.06399 -0.0134 0.0533 1.0000
13.500 1.2747 0.07522 0.06871 -0.0129 0.0535 1.0000
13.750 1.2576 0.08002 0.07378 -0.0129 0.0537 1.0000
14.000 1.2384 0.08521 0.07923 -0.0135 0.0540 1.0000
14.250 1.2174 0.09084 0.08508 -0.0147 0.0543 1.0000
14.500 1.1954 0.09691 0.09135 -0.0164 0.0547 1.0000
14.750 1.1731 0.10345 0.09807 -0.0187 0.0551 1.0000
15.000 1.1522 0.11041 0.10518 -0.0214 0.0556 1.0000
15.250 1.1369 0.11743 0.11235 -0.0240 0.0562 1.0000
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