BOEING-VERTOL VR-7 AIRFOIL (vr7-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-7 AIRFOIL (vr7-il) Reynolds number: 500,000 Max Cl/Cd: 96.22 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-vr7-il-500000-n5.txt Download as CSV file: xf-vr7-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4519 0.07870 0.07646 -0.0379 1.0000 0.0103
-9.750 -0.4715 0.07028 0.06808 -0.0435 1.0000 0.0102
-9.500 -0.5210 0.05633 0.05407 -0.0553 0.9984 0.0102
-9.250 -0.5106 0.04733 0.04471 -0.0662 0.9283 0.0104
-9.000 -0.5019 0.04325 0.04024 -0.0684 0.8666 0.0106
-8.750 -0.5024 0.04022 0.03684 -0.0667 0.8232 0.0108
-8.500 -0.5020 0.03666 0.03291 -0.0648 0.7959 0.0110
-8.250 -0.5048 0.03145 0.02718 -0.0624 0.7767 0.0113
-8.000 -0.5037 0.02621 0.02129 -0.0596 0.7622 0.0118
-7.750 -0.4934 0.02256 0.01702 -0.0574 0.7502 0.0124
-7.500 -0.4751 0.02063 0.01464 -0.0561 0.7392 0.0128
-7.250 -0.4543 0.01933 0.01311 -0.0551 0.7292 0.0132
-7.000 -0.4312 0.01870 0.01236 -0.0545 0.7198 0.0136
-6.750 -0.4073 0.01805 0.01159 -0.0539 0.7113 0.0139
-6.500 -0.3835 0.01728 0.01064 -0.0533 0.7040 0.0142
-6.250 -0.3591 0.01651 0.00973 -0.0527 0.6970 0.0146
-6.000 -0.3346 0.01580 0.00887 -0.0521 0.6905 0.0150
-5.750 -0.3099 0.01511 0.00805 -0.0515 0.6843 0.0154
-5.500 -0.2850 0.01451 0.00733 -0.0509 0.6774 0.0157
-5.250 -0.2596 0.01409 0.00678 -0.0504 0.6710 0.0162
-5.000 -0.2351 0.01347 0.00609 -0.0498 0.6642 0.0167
-4.750 -0.2102 0.01302 0.00559 -0.0492 0.6583 0.0172
-4.500 -0.1848 0.01262 0.00515 -0.0488 0.6529 0.0175
-4.250 -0.1592 0.01226 0.00474 -0.0483 0.6472 0.0181
-4.000 -0.1337 0.01195 0.00436 -0.0478 0.6414 0.0186
-3.750 -0.1077 0.01164 0.00400 -0.0474 0.6359 0.0192
-3.500 -0.0816 0.01136 0.00367 -0.0470 0.6309 0.0199
-3.250 -0.0555 0.01110 0.00335 -0.0466 0.6264 0.0206
-3.000 -0.0292 0.01085 0.00309 -0.0462 0.6217 0.0220
-2.750 -0.0025 0.01065 0.00287 -0.0460 0.6163 0.0234
-2.500 0.0242 0.01049 0.00265 -0.0457 0.6111 0.0249
-2.250 0.0510 0.01030 0.00245 -0.0454 0.6064 0.0275
-2.000 0.0781 0.01015 0.00229 -0.0451 0.6011 0.0315
-1.750 0.1049 0.01000 0.00214 -0.0449 0.5957 0.0397
-1.500 0.1315 0.00981 0.00202 -0.0446 0.5904 0.0625
-1.250 0.1563 0.00935 0.00187 -0.0442 0.5844 0.1620
-1.000 0.1796 0.00875 0.00173 -0.0436 0.5788 0.3118
-0.750 0.2006 0.00803 0.00169 -0.0425 0.5729 0.5235
-0.500 0.2253 0.00781 0.00168 -0.0419 0.5665 0.5951
0.000 0.2746 0.00745 0.00168 -0.0403 0.5540 0.7106
0.250 0.2984 0.00730 0.00170 -0.0393 0.5479 0.7715
0.500 0.3239 0.00719 0.00173 -0.0386 0.5413 0.8159
0.750 0.3504 0.00715 0.00176 -0.0381 0.5345 0.8563
1.250 0.4146 0.00719 0.00186 -0.0395 0.5203 0.9223
1.500 0.4524 0.00727 0.00191 -0.0416 0.5118 0.9424
1.750 0.4903 0.00738 0.00196 -0.0437 0.5023 0.9578
2.000 0.5275 0.00746 0.00201 -0.0457 0.4934 0.9680
2.250 0.5623 0.00757 0.00206 -0.0473 0.4838 0.9749
2.500 0.5952 0.00769 0.00212 -0.0484 0.4726 0.9818
2.750 0.6290 0.00780 0.00219 -0.0498 0.4624 0.9871
3.000 0.6627 0.00792 0.00227 -0.0512 0.4539 0.9921
3.250 0.6965 0.00803 0.00236 -0.0526 0.4444 0.9964
3.500 0.7308 0.00815 0.00244 -0.0541 0.4342 0.9998
3.750 0.7551 0.00829 0.00254 -0.0535 0.4234 1.0000
4.000 0.7784 0.00844 0.00266 -0.0526 0.4112 1.0000
4.250 0.8018 0.00860 0.00278 -0.0518 0.3995 1.0000
4.500 0.8251 0.00877 0.00292 -0.0510 0.3897 1.0000
4.750 0.8481 0.00897 0.00308 -0.0501 0.3787 1.0000
5.000 0.8716 0.00915 0.00324 -0.0494 0.3685 1.0000
5.250 0.8952 0.00933 0.00341 -0.0486 0.3591 1.0000
5.500 0.9182 0.00955 0.00360 -0.0478 0.3462 1.0000
5.750 0.9410 0.00978 0.00381 -0.0469 0.3310 1.0000
6.000 0.9637 0.01002 0.00402 -0.0460 0.3167 1.0000
6.250 0.9860 0.01030 0.00425 -0.0451 0.3005 1.0000
6.500 1.0079 0.01060 0.00452 -0.0441 0.2836 1.0000
6.750 1.0281 0.01102 0.00483 -0.0429 0.2598 1.0000
7.000 1.0460 0.01160 0.00524 -0.0414 0.2240 1.0000
7.250 1.0621 0.01231 0.00575 -0.0397 0.1882 1.0000
7.500 1.0802 0.01287 0.00621 -0.0382 0.1651 1.0000
7.750 1.0976 0.01347 0.00669 -0.0367 0.1404 1.0000
8.000 1.1151 0.01405 0.00717 -0.0352 0.1220 1.0000
8.250 1.1328 0.01459 0.00766 -0.0338 0.1041 1.0000
8.500 1.1489 0.01521 0.00820 -0.0321 0.0876 1.0000
8.750 1.1654 0.01577 0.00873 -0.0305 0.0769 1.0000
9.000 1.1813 0.01634 0.00928 -0.0289 0.0688 1.0000
9.250 1.1974 0.01686 0.00981 -0.0272 0.0629 1.0000
9.500 1.2110 0.01744 0.01039 -0.0252 0.0576 1.0000
9.750 1.2234 0.01796 0.01095 -0.0229 0.0531 1.0000
10.000 1.2332 0.01862 0.01161 -0.0203 0.0488 1.0000
10.250 1.2456 0.01919 0.01223 -0.0183 0.0452 1.0000
10.500 1.2555 0.01994 0.01301 -0.0162 0.0405 1.0000
10.750 1.2652 0.02076 0.01385 -0.0142 0.0367 1.0000
11.000 1.2732 0.02175 0.01485 -0.0122 0.0330 1.0000
11.250 1.2822 0.02276 0.01591 -0.0106 0.0305 1.0000
11.500 1.2900 0.02393 0.01712 -0.0091 0.0280 1.0000
11.750 1.2961 0.02532 0.01855 -0.0077 0.0260 1.0000
12.000 1.3047 0.02662 0.01993 -0.0067 0.0246 1.0000
12.250 1.3121 0.02808 0.02146 -0.0058 0.0235 1.0000
12.500 1.3178 0.02976 0.02320 -0.0049 0.0223 1.0000
12.750 1.3214 0.03170 0.02518 -0.0042 0.0210 1.0000
13.000 1.3272 0.03350 0.02707 -0.0036 0.0205 1.0000
13.250 1.3330 0.03534 0.02900 -0.0032 0.0198 1.0000
13.500 1.3372 0.03737 0.03112 -0.0027 0.0192 1.0000
13.750 1.3405 0.03952 0.03335 -0.0024 0.0184 1.0000
14.000 1.3424 0.04185 0.03575 -0.0022 0.0178 1.0000
14.250 1.3428 0.04439 0.03836 -0.0020 0.0173 1.0000
14.500 1.3398 0.04733 0.04138 -0.0020 0.0167 1.0000
14.750 1.3420 0.04981 0.04396 -0.0020 0.0163 1.0000
15.000 1.3416 0.05265 0.04690 -0.0022 0.0160 1.0000
15.250 1.3429 0.05536 0.04970 -0.0025 0.0154 1.0000
15.500 1.3425 0.05837 0.05281 -0.0030 0.0151 1.0000
15.750 1.3412 0.06158 0.05611 -0.0035 0.0147 1.0000
16.000 1.3389 0.06498 0.05961 -0.0042 0.0144 1.0000
16.250 1.3356 0.06859 0.06331 -0.0051 0.0140 1.0000
16.500 1.3315 0.07240 0.06720 -0.0061 0.0136 1.0000
16.750 1.3254 0.07658 0.07147 -0.0073 0.0134 1.0000
17.000 1.3190 0.08086 0.07584 -0.0086 0.0131 1.0000
17.250 1.3164 0.08468 0.07978 -0.0099 0.0128 1.0000
17.500 1.3130 0.08870 0.08391 -0.0112 0.0125 1.0000
17.750 1.3093 0.09282 0.08813 -0.0127 0.0122 1.0000
18.000 1.3042 0.09719 0.09261 -0.0144 0.0119 1.0000
18.250 1.2984 0.10174 0.09726 -0.0162 0.0117 1.0000
18.500 1.2921 0.10648 0.10210 -0.0181 0.0114 1.0000
18.750 1.2858 0.11132 0.10704 -0.0202 0.0111 1.0000
19.000 1.2784 0.11636 0.11218 -0.0225 0.0109 1.0000
19.250 1.2705 0.12159 0.11750 -0.0250 0.0107 1.0000
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Polar data table (+)
Polar graphs
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