BOEING-VERTOL VR-7 AIRFOIL (vr7-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-7 AIRFOIL (vr7-il) Reynolds number: 1,000,000 Max Cl/Cd: 125.01 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-vr7-il-1000000.txt Download as CSV file: xf-vr7-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4182 0.08187 0.08032 -0.0341 1.0000 0.0140
-9.250 -0.4216 0.07721 0.07568 -0.0369 1.0000 0.0144
-9.000 -0.4307 0.07140 0.06990 -0.0411 1.0000 0.0145
-8.750 -0.4439 0.06198 0.06045 -0.0537 0.9728 0.0144
-8.250 -0.4314 0.03054 0.02783 -0.0615 0.7809 0.0159
-8.000 -0.4560 0.02289 0.01980 -0.0592 0.7653 0.0164
-7.750 -0.4457 0.02073 0.01748 -0.0581 0.7513 0.0165
-7.500 -0.4290 0.01977 0.01644 -0.0575 0.7388 0.0168
-7.250 -0.4389 0.02580 0.02165 -0.0581 0.7494 0.0150
-6.750 -0.4142 0.01806 0.01287 -0.0535 0.7281 0.0145
-6.500 -0.3920 0.01671 0.01126 -0.0524 0.7190 0.0149
-6.250 -0.3676 0.01598 0.01035 -0.0518 0.7099 0.0155
-6.000 -0.3425 0.01542 0.00962 -0.0511 0.7020 0.0158
-5.750 -0.3188 0.01417 0.00817 -0.0504 0.6945 0.0161
-5.500 -0.2953 0.01299 0.00690 -0.0496 0.6881 0.0166
-5.250 -0.2703 0.01239 0.00624 -0.0491 0.6814 0.0169
-4.750 -0.2193 0.01151 0.00526 -0.0481 0.6694 0.0178
-4.500 -0.1936 0.01113 0.00482 -0.0476 0.6635 0.0183
-4.250 -0.1678 0.01080 0.00444 -0.0471 0.6582 0.0190
-4.000 -0.1411 0.01055 0.00416 -0.0468 0.6532 0.0196
-3.750 -0.1149 0.01028 0.00382 -0.0464 0.6483 0.0200
-3.500 -0.0911 0.00969 0.00316 -0.0456 0.6435 0.0210
-3.250 -0.0645 0.00941 0.00288 -0.0453 0.6387 0.0218
-3.000 -0.0377 0.00921 0.00265 -0.0450 0.6336 0.0229
-2.750 -0.0111 0.00906 0.00243 -0.0446 0.6284 0.0240
-2.500 0.0160 0.00883 0.00219 -0.0444 0.6238 0.0256
-2.250 0.0430 0.00865 0.00200 -0.0441 0.6185 0.0284
-2.000 0.0700 0.00854 0.00185 -0.0439 0.6132 0.0313
-1.750 0.0972 0.00833 0.00167 -0.0436 0.6081 0.0409
-1.500 0.1232 0.00801 0.00152 -0.0433 0.6026 0.0918
-1.250 0.1454 0.00730 0.00137 -0.0425 0.5972 0.2784
-1.000 0.1664 0.00647 0.00128 -0.0415 0.5920 0.5057
-0.750 0.1923 0.00629 0.00126 -0.0410 0.5861 0.5697
-0.500 0.2183 0.00617 0.00124 -0.0406 0.5805 0.6167
-0.250 0.2443 0.00601 0.00123 -0.0401 0.5744 0.6657
0.000 0.2684 0.00582 0.00124 -0.0392 0.5683 0.7349
0.250 0.2923 0.00563 0.00126 -0.0382 0.5624 0.8007
0.500 0.3166 0.00550 0.00129 -0.0372 0.5557 0.8607
0.750 0.3439 0.00544 0.00135 -0.0368 0.5484 0.9150
1.000 0.3775 0.00547 0.00139 -0.0378 0.5402 0.9430
1.250 0.4146 0.00555 0.00144 -0.0398 0.5329 0.9589
1.500 0.4520 0.00564 0.00149 -0.0418 0.5252 0.9715
1.750 0.4921 0.00574 0.00154 -0.0444 0.5176 0.9772
2.000 0.5248 0.00583 0.00160 -0.0454 0.5092 0.9834
2.250 0.5628 0.00591 0.00164 -0.0477 0.5008 0.9859
2.500 0.5994 0.00602 0.00168 -0.0496 0.4904 0.9892
2.750 0.6348 0.00611 0.00174 -0.0513 0.4798 0.9927
3.000 0.6710 0.00620 0.00179 -0.0532 0.4702 0.9954
3.250 0.7078 0.00630 0.00184 -0.0553 0.4607 0.9979
3.500 0.7443 0.00639 0.00190 -0.0573 0.4485 0.9999
3.750 0.7685 0.00648 0.00197 -0.0566 0.4379 1.0000
4.000 0.7919 0.00660 0.00204 -0.0558 0.4280 1.0000
4.500 0.8390 0.00684 0.00223 -0.0542 0.4064 1.0000
4.750 0.8625 0.00699 0.00234 -0.0533 0.3960 1.0000
5.000 0.8856 0.00716 0.00247 -0.0525 0.3846 1.0000
5.250 0.9092 0.00731 0.00261 -0.0517 0.3747 1.0000
5.500 0.9329 0.00747 0.00275 -0.0509 0.3645 1.0000
5.750 0.9563 0.00765 0.00291 -0.0501 0.3546 1.0000
6.000 0.9797 0.00784 0.00307 -0.0494 0.3420 1.0000
6.250 1.0024 0.00808 0.00325 -0.0485 0.3206 1.0000
6.500 1.0237 0.00842 0.00347 -0.0474 0.2960 1.0000
6.750 1.0443 0.00881 0.00374 -0.0462 0.2686 1.0000
7.000 1.0641 0.00927 0.00406 -0.0449 0.2378 1.0000
7.250 1.0825 0.00982 0.00444 -0.0434 0.2031 1.0000
7.500 1.1014 0.01032 0.00482 -0.0420 0.1800 1.0000
7.750 1.1215 0.01074 0.00517 -0.0407 0.1617 1.0000
8.000 1.1397 0.01128 0.00559 -0.0393 0.1372 1.0000
8.250 1.1572 0.01185 0.00604 -0.0377 0.1151 1.0000
8.500 1.1738 0.01248 0.00653 -0.0360 0.0913 1.0000
8.750 1.1911 0.01303 0.00700 -0.0344 0.0766 1.0000
9.000 1.2095 0.01351 0.00745 -0.0330 0.0679 1.0000
9.250 1.2280 0.01395 0.00789 -0.0317 0.0611 1.0000
9.500 1.2452 0.01446 0.00837 -0.0301 0.0543 1.0000
9.750 1.2624 0.01493 0.00884 -0.0286 0.0481 1.0000
10.000 1.2780 0.01546 0.00935 -0.0268 0.0408 1.0000
10.250 1.2897 0.01609 0.00994 -0.0245 0.0336 1.0000
10.500 1.2981 0.01672 0.01056 -0.0215 0.0291 1.0000
10.750 1.3081 0.01733 0.01118 -0.0189 0.0266 1.0000
11.000 1.3147 0.01817 0.01204 -0.0160 0.0238 1.0000
11.250 1.3264 0.01882 0.01275 -0.0141 0.0229 1.0000
11.500 1.3368 0.01960 0.01358 -0.0122 0.0216 1.0000
11.750 1.3454 0.02056 0.01458 -0.0104 0.0206 1.0000
12.000 1.3501 0.02188 0.01595 -0.0084 0.0194 1.0000
12.250 1.3593 0.02301 0.01714 -0.0071 0.0187 1.0000
12.500 1.3691 0.02418 0.01838 -0.0061 0.0181 1.0000
12.750 1.3779 0.02551 0.01978 -0.0052 0.0175 1.0000
13.000 1.3854 0.02704 0.02137 -0.0045 0.0168 1.0000
13.250 1.3914 0.02877 0.02316 -0.0038 0.0162 1.0000
13.500 1.3928 0.03100 0.02546 -0.0032 0.0156 1.0000
13.750 1.3930 0.03341 0.02796 -0.0027 0.0149 1.0000
14.000 1.4004 0.03516 0.02978 -0.0024 0.0146 1.0000
14.250 1.4053 0.03719 0.03189 -0.0022 0.0143 1.0000
14.500 1.4086 0.03940 0.03418 -0.0020 0.0140 1.0000
14.750 1.4108 0.04173 0.03659 -0.0018 0.0137 1.0000
15.000 1.4127 0.04413 0.03906 -0.0017 0.0132 1.0000
15.250 1.4122 0.04685 0.04185 -0.0017 0.0129 1.0000
15.500 1.4098 0.04983 0.04491 -0.0019 0.0126 1.0000
15.750 1.4046 0.05329 0.04845 -0.0023 0.0123 1.0000
16.000 1.3944 0.05742 0.05268 -0.0028 0.0120 1.0000
16.250 1.3838 0.06173 0.05710 -0.0035 0.0118 1.0000
16.500 1.3819 0.06508 0.06053 -0.0042 0.0116 1.0000
16.750 1.3823 0.06815 0.06369 -0.0049 0.0114 1.0000
17.000 1.3787 0.07181 0.06744 -0.0057 0.0112 1.0000
17.250 1.3772 0.07526 0.07098 -0.0066 0.0109 1.0000
17.500 1.3728 0.07914 0.07495 -0.0077 0.0108 1.0000
17.750 1.3658 0.08343 0.07933 -0.0089 0.0106 1.0000
18.000 1.3637 0.08712 0.08309 -0.0101 0.0103 1.0000
18.250 1.3563 0.09163 0.08769 -0.0116 0.0102 1.0000
18.500 1.3494 0.09614 0.09229 -0.0132 0.0100 1.0000
18.750 1.3418 0.10080 0.09703 -0.0149 0.0098 1.0000
19.000 1.3331 0.10574 0.10205 -0.0169 0.0096 1.0000
19.250 1.3226 0.11107 0.10746 -0.0190 0.0095 1.0000
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Polar data table (+)
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