BOEING-VERTOL VR-7 AIRFOIL (vr7-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-7 AIRFOIL (vr7-il) Reynolds number: 100,000 Max Cl/Cd: 53.45 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-vr7-il-100000-n5.txt Download as CSV file: xf-vr7-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BOEING-VERTOL VR-7 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4254 0.07434 0.06961 -0.0498 1.0000 0.0380
-8.500 -0.4279 0.07146 0.06678 -0.0491 1.0000 0.0375
-8.250 -0.4327 0.06827 0.06363 -0.0487 1.0000 0.0369
-8.000 -0.4409 0.06480 0.06016 -0.0483 1.0000 0.0363
-7.750 -0.4499 0.06153 0.05689 -0.0472 1.0000 0.0355
-7.500 -0.4446 0.05594 0.05108 -0.0503 0.9825 0.0340
-7.000 -0.4134 0.04262 0.03628 -0.0568 0.9377 0.0309
-6.750 -0.3899 0.03894 0.03214 -0.0582 0.9201 0.0312
-6.500 -0.3628 0.03672 0.02987 -0.0598 0.9041 0.0325
-6.250 -0.3376 0.03452 0.02735 -0.0605 0.8875 0.0338
-6.000 -0.3138 0.03205 0.02442 -0.0603 0.8718 0.0343
-5.750 -0.2898 0.02980 0.02170 -0.0598 0.8572 0.0345
-5.500 -0.2652 0.02790 0.01939 -0.0592 0.8441 0.0348
-5.250 -0.2399 0.02624 0.01734 -0.0586 0.8322 0.0353
-5.000 -0.2146 0.02487 0.01565 -0.0578 0.8202 0.0365
-4.750 -0.1884 0.02389 0.01427 -0.0571 0.8096 0.0383
-4.500 -0.1625 0.02252 0.01283 -0.0568 0.8002 0.0396
-4.250 -0.1367 0.02150 0.01173 -0.0563 0.7902 0.0408
-4.000 -0.1105 0.02062 0.01075 -0.0558 0.7820 0.0422
-3.750 -0.0854 0.01984 0.00991 -0.0551 0.7729 0.0440
-3.500 -0.0602 0.01926 0.00918 -0.0544 0.7650 0.0471
-3.250 -0.0370 0.01859 0.00852 -0.0536 0.7565 0.0508
-3.000 -0.0128 0.01810 0.00793 -0.0527 0.7488 0.0548
-2.750 0.0111 0.01763 0.00737 -0.0518 0.7399 0.0606
-2.500 0.0352 0.01716 0.00682 -0.0510 0.7314 0.0726
-2.250 0.0580 0.01645 0.00631 -0.0500 0.7230 0.1131
-2.000 0.0708 0.01452 0.00617 -0.0478 0.7156 0.5382
-1.750 0.0912 0.01404 0.00626 -0.0454 0.7083 0.7052
-1.500 0.1211 0.01388 0.00642 -0.0440 0.7018 0.8299
-1.250 0.1678 0.01402 0.00653 -0.0462 0.6942 0.9022
-1.000 0.2115 0.01411 0.00639 -0.0489 0.6879 0.9304
-0.750 0.2519 0.01417 0.00630 -0.0515 0.6799 0.9471
-0.500 0.2923 0.01420 0.00612 -0.0540 0.6734 0.9611
-0.250 0.3326 0.01424 0.00604 -0.0568 0.6654 0.9751
0.000 0.3734 0.01426 0.00589 -0.0596 0.6585 0.9881
0.250 0.4139 0.01428 0.00581 -0.0626 0.6508 1.0000
0.500 0.4346 0.01436 0.00577 -0.0615 0.6437 1.0000
0.750 0.4558 0.01446 0.00580 -0.0604 0.6366 1.0000
1.000 0.4774 0.01457 0.00584 -0.0594 0.6293 1.0000
1.250 0.4998 0.01470 0.00587 -0.0585 0.6226 1.0000
1.500 0.5218 0.01484 0.00598 -0.0575 0.6146 1.0000
1.750 0.5451 0.01497 0.00601 -0.0566 0.6085 1.0000
2.000 0.5671 0.01514 0.00619 -0.0557 0.6001 1.0000
2.250 0.5908 0.01527 0.00624 -0.0548 0.5938 1.0000
2.500 0.6132 0.01547 0.00647 -0.0539 0.5855 1.0000
2.750 0.6370 0.01561 0.00655 -0.0531 0.5788 1.0000
3.000 0.6596 0.01582 0.00678 -0.0522 0.5707 1.0000
3.250 0.6835 0.01596 0.00691 -0.0514 0.5638 1.0000
3.500 0.7063 0.01618 0.00716 -0.0506 0.5556 1.0000
3.750 0.7303 0.01634 0.00729 -0.0498 0.5486 1.0000
4.000 0.7530 0.01656 0.00755 -0.0489 0.5397 1.0000
4.250 0.7773 0.01669 0.00767 -0.0481 0.5323 1.0000
4.500 0.7997 0.01693 0.00798 -0.0472 0.5224 1.0000
4.750 0.8232 0.01710 0.00815 -0.0464 0.5136 1.0000
5.000 0.8463 0.01729 0.00839 -0.0455 0.5038 1.0000
5.250 0.8691 0.01752 0.00868 -0.0446 0.4940 1.0000
5.500 0.8929 0.01771 0.00886 -0.0438 0.4853 1.0000
5.750 0.9152 0.01797 0.00923 -0.0429 0.4747 1.0000
6.000 0.9377 0.01822 0.00954 -0.0419 0.4641 1.0000
6.250 0.9605 0.01844 0.00979 -0.0410 0.4537 1.0000
6.500 0.9826 0.01874 0.01018 -0.0401 0.4429 1.0000
6.750 1.0041 0.01903 0.01058 -0.0390 0.4308 1.0000
7.000 1.0245 0.01928 0.01087 -0.0378 0.4150 1.0000
7.250 1.0439 0.01953 0.01111 -0.0363 0.3966 1.0000
7.500 1.0624 0.01989 0.01149 -0.0348 0.3776 1.0000
7.750 1.0810 0.02031 0.01196 -0.0334 0.3608 1.0000
8.000 1.0992 0.02077 0.01251 -0.0320 0.3444 1.0000
8.250 1.1162 0.02127 0.01308 -0.0305 0.3262 1.0000
8.500 1.1312 0.02184 0.01367 -0.0286 0.3054 1.0000
8.750 1.1438 0.02252 0.01435 -0.0266 0.2801 1.0000
9.000 1.1532 0.02335 0.01512 -0.0242 0.2527 1.0000
9.250 1.1594 0.02436 0.01603 -0.0215 0.2253 1.0000
9.500 1.1609 0.02551 0.01706 -0.0183 0.2004 1.0000
9.750 1.1600 0.02683 0.01829 -0.0150 0.1805 1.0000
10.000 1.1594 0.02831 0.01971 -0.0122 0.1621 1.0000
10.250 1.1595 0.02991 0.02130 -0.0099 0.1443 1.0000
10.500 1.1583 0.03175 0.02310 -0.0079 0.1291 1.0000
10.750 1.1568 0.03379 0.02510 -0.0063 0.1172 1.0000
11.000 1.1562 0.03592 0.02724 -0.0051 0.1057 1.0000
11.250 1.1565 0.03810 0.02946 -0.0041 0.0966 1.0000
11.500 1.1558 0.04046 0.03186 -0.0033 0.0895 1.0000
11.750 1.1542 0.04300 0.03443 -0.0027 0.0832 1.0000
12.000 1.1537 0.04552 0.03700 -0.0022 0.0779 1.0000
12.250 1.1535 0.04807 0.03964 -0.0017 0.0730 1.0000
12.500 1.1501 0.05099 0.04254 -0.0015 0.0689 1.0000
12.750 1.1521 0.05346 0.04516 -0.0012 0.0644 1.0000
13.000 1.1516 0.05621 0.04798 -0.0011 0.0610 1.0000
13.500 1.1530 0.06157 0.05349 -0.0008 0.0554 1.0000
13.750 1.1549 0.06424 0.05629 -0.0007 0.0525 1.0000
14.000 1.1557 0.06707 0.05918 -0.0009 0.0503 1.0000
14.250 1.1571 0.06981 0.06191 -0.0010 0.0482 1.0000
14.500 1.1594 0.07272 0.06503 -0.0012 0.0460 1.0000
14.750 1.1617 0.07563 0.06811 -0.0015 0.0441 1.0000
15.000 1.1635 0.07863 0.07123 -0.0019 0.0425 1.0000
15.250 1.1644 0.08179 0.07447 -0.0026 0.0411 1.0000
15.500 1.1663 0.08478 0.07751 -0.0031 0.0399 1.0000
15.750 1.1654 0.08841 0.08131 -0.0040 0.0387 1.0000
16.000 1.1612 0.09272 0.08587 -0.0054 0.0375 1.0000
16.250 1.1559 0.09730 0.09066 -0.0071 0.0364 1.0000
16.500 1.1507 0.10192 0.09547 -0.0089 0.0356 1.0000
16.750 1.1446 0.10677 0.10048 -0.0110 0.0348 1.0000
17.000 1.1382 0.11178 0.10563 -0.0133 0.0341 1.0000
17.250 1.1325 0.11671 0.11068 -0.0156 0.0334 1.0000
17.500 1.1286 0.12133 0.11538 -0.0179 0.0327 1.0000
17.750 1.1225 0.12644 0.12057 -0.0205 0.0321 1.0000
18.000 1.1035 0.13479 0.12916 -0.0254 0.0319 1.0000
18.250 1.0809 0.14443 0.13902 -0.0312 0.0318 1.0000
18.500 1.0551 0.15551 0.15027 -0.0380 0.0320 1.0000
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Polar data table (+)
Polar graphs
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