BOEING-VERTOL VR-1 AIRFOIL (vr1-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-1 AIRFOIL (vr1-il) Reynolds number: 200,000 Max Cl/Cd: 63.46 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-vr1-il-200000.txt Download as CSV file: xf-vr1-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: BOEING-VERTOL VR-1 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4871 0.10416 0.10019 -0.0309 1.0000 0.0672
-10.500 -0.5139 0.09669 0.09281 -0.0399 1.0000 0.0704
-10.250 -0.5620 0.08658 0.08270 -0.0526 1.0000 0.0708
-10.000 -0.5195 0.08722 0.08342 -0.0424 1.0000 0.0725
-9.750 -0.5083 0.08553 0.08173 -0.0406 1.0000 0.0738
-9.500 -0.5069 0.08234 0.07857 -0.0412 1.0000 0.0754
-9.250 -0.5151 0.07765 0.07394 -0.0440 1.0000 0.0772
-9.000 -0.5418 0.07115 0.06746 -0.0493 1.0000 0.0782
-8.750 -0.5719 0.06730 0.06359 -0.0483 1.0000 0.0791
-8.500 -0.6266 0.06428 0.06025 -0.0450 1.0000 0.0821
-8.000 -0.6516 0.05724 0.05313 -0.0386 1.0000 0.0845
-7.750 -0.6477 0.05532 0.05128 -0.0358 1.0000 0.0856
-7.500 -0.6489 0.05365 0.04961 -0.0325 1.0000 0.0872
-7.250 -0.6526 0.05192 0.04782 -0.0291 1.0000 0.0894
-7.000 -0.6666 0.04922 0.04456 -0.0261 0.9985 0.0971
-6.750 -0.6370 0.04594 0.04142 -0.0282 0.9953 0.0997
-6.500 -0.6140 0.04337 0.03836 -0.0302 0.9889 0.1113
-6.250 -0.5894 0.02960 0.02253 -0.0276 0.9845 0.0501
-6.000 -0.5612 0.02692 0.01962 -0.0282 0.9797 0.0492
-5.750 -0.5286 0.02464 0.01706 -0.0294 0.9756 0.0478
-5.500 -0.4924 0.02276 0.01490 -0.0310 0.9728 0.0466
-5.250 -0.4611 0.02142 0.01338 -0.0316 0.9680 0.0462
-5.000 -0.4276 0.02026 0.01210 -0.0327 0.9634 0.0463
-4.750 -0.3907 0.01922 0.01102 -0.0345 0.9602 0.0468
-4.500 -0.3517 0.01837 0.01014 -0.0368 0.9578 0.0484
-4.250 -0.3256 0.01778 0.00951 -0.0365 0.9505 0.0498
-4.000 -0.2909 0.01696 0.00870 -0.0379 0.9464 0.0513
-3.750 -0.2539 0.01607 0.00787 -0.0400 0.9436 0.0537
-3.500 -0.2255 0.01559 0.00738 -0.0403 0.9375 0.0567
-3.250 -0.1927 0.01510 0.00686 -0.0413 0.9323 0.0616
-3.000 -0.1568 0.01437 0.00630 -0.0430 0.9289 0.0853
-2.750 -0.1424 0.01252 0.00592 -0.0414 0.9219 0.3902
-2.500 -0.1240 0.01168 0.00589 -0.0394 0.9150 0.5792
-2.250 -0.0954 0.01124 0.00596 -0.0388 0.9114 0.7123
-2.000 -0.0727 0.01121 0.00614 -0.0369 0.9045 0.7815
-1.750 -0.0446 0.01123 0.00625 -0.0360 0.8990 0.8291
-1.500 -0.0103 0.01126 0.00628 -0.0364 0.8954 0.8616
-1.250 0.0223 0.01146 0.00648 -0.0363 0.8909 0.8925
-1.000 0.0621 0.01179 0.00680 -0.0375 0.8860 0.9173
-0.750 0.1075 0.01193 0.00689 -0.0403 0.8823 0.9310
-0.500 0.1558 0.01197 0.00687 -0.0441 0.8792 0.9393
-0.250 0.2009 0.01197 0.00682 -0.0474 0.8752 0.9459
0.000 0.2449 0.01202 0.00685 -0.0506 0.8689 0.9526
0.250 0.2883 0.01199 0.00679 -0.0536 0.8639 0.9607
0.500 0.3356 0.01192 0.00670 -0.0574 0.8597 0.9670
0.750 0.3751 0.01186 0.00665 -0.0597 0.8498 0.9751
1.000 0.4166 0.01165 0.00641 -0.0621 0.8391 0.9823
1.250 0.4600 0.01134 0.00606 -0.0648 0.8272 0.9887
1.500 0.5021 0.01104 0.00575 -0.0674 0.8119 0.9962
1.750 0.5332 0.01075 0.00540 -0.0678 0.7937 1.0000
2.000 0.5496 0.01059 0.00521 -0.0653 0.7735 1.0000
2.250 0.5673 0.01046 0.00505 -0.0631 0.7541 1.0000
2.500 0.5858 0.01036 0.00493 -0.0610 0.7350 1.0000
2.750 0.6046 0.01028 0.00479 -0.0590 0.7136 1.0000
3.000 0.6224 0.01024 0.00474 -0.0568 0.6874 1.0000
3.250 0.6396 0.01023 0.00465 -0.0543 0.6535 1.0000
3.500 0.6549 0.01032 0.00457 -0.0515 0.6015 1.0000
3.750 0.6625 0.01081 0.00452 -0.0473 0.4851 1.0000
4.000 0.6540 0.01243 0.00500 -0.0409 0.2723 1.0000
4.500 0.6646 0.01465 0.00624 -0.0333 0.1279 1.0000
4.750 0.6764 0.01536 0.00685 -0.0304 0.1114 1.0000
5.000 0.6898 0.01603 0.00744 -0.0278 0.0997 1.0000
5.250 0.7048 0.01665 0.00806 -0.0254 0.0909 1.0000
5.500 0.7175 0.01757 0.00886 -0.0228 0.0841 1.0000
5.750 0.7357 0.01807 0.00941 -0.0210 0.0784 1.0000
6.000 0.7522 0.01885 0.01010 -0.0191 0.0737 1.0000
6.250 0.7713 0.01977 0.01104 -0.0175 0.0703 1.0000
6.500 0.7920 0.02052 0.01181 -0.0162 0.0672 1.0000
6.750 0.8129 0.02128 0.01255 -0.0151 0.0643 1.0000
7.000 0.8374 0.02284 0.01401 -0.0148 0.0614 1.0000
7.250 0.8596 0.02359 0.01491 -0.0137 0.0597 1.0000
7.500 0.8832 0.02467 0.01610 -0.0129 0.0580 1.0000
7.750 0.9070 0.02587 0.01740 -0.0123 0.0564 1.0000
8.000 0.9301 0.02711 0.01874 -0.0116 0.0552 1.0000
8.250 0.9523 0.02837 0.02003 -0.0109 0.0538 1.0000
8.500 0.9767 0.03091 0.02262 -0.0109 0.0523 1.0000
8.750 0.9942 0.03258 0.02457 -0.0093 0.0516 1.0000
9.000 1.0104 0.03451 0.02681 -0.0076 0.0512 1.0000
9.250 1.0248 0.03691 0.02951 -0.0058 0.0509 1.0000
9.500 1.0362 0.03961 0.03253 -0.0038 0.0509 1.0000
9.750 1.0443 0.04250 0.03573 -0.0014 0.0510 1.0000
10.000 1.0483 0.04551 0.03907 0.0012 0.0509 1.0000
10.250 1.0490 0.04870 0.04257 0.0040 0.0510 1.0000
10.500 1.0473 0.05214 0.04628 0.0068 0.0512 1.0000
10.750 1.0581 0.05698 0.05118 0.0073 0.0523 1.0000
11.000 0.9584 0.08257 0.07801 0.0137 0.0846 1.0000
11.250 0.9281 0.08487 0.08046 0.0175 0.0845 1.0000
11.500 0.8963 0.08803 0.08375 0.0191 0.0844 1.0000
11.750 0.8588 0.09243 0.08828 0.0184 0.0843 1.0000
12.000 0.8194 0.09893 0.09487 0.0148 0.0842 1.0000
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Polar data table (+)
Polar graphs
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