BOEING-VERTOL VR-7 AIRFOIL (vr7-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-7 AIRFOIL (vr7-il) Reynolds number: 500,000 Max Cl/Cd: 103.05 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-vr7-il-500000.txt Download as CSV file: xf-vr7-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3993 0.08619 0.08398 -0.0337 1.0000 0.0220
-9.250 -0.4008 0.08207 0.07989 -0.0359 1.0000 0.0227
-9.000 -0.4056 0.07732 0.07518 -0.0387 1.0000 0.0230
-8.750 -0.4147 0.07170 0.06961 -0.0432 1.0000 0.0235
-8.000 -0.4577 0.04836 0.04549 -0.0587 0.9645 0.0250
-7.750 -0.4276 0.04358 0.04066 -0.0639 0.9387 0.0255
-7.500 -0.4013 0.04108 0.03798 -0.0665 0.8967 0.0261
-7.250 -0.3891 0.03893 0.03555 -0.0655 0.8551 0.0267
-7.000 -0.3774 0.03680 0.03312 -0.0640 0.8260 0.0279
-6.750 -0.3629 0.03622 0.03182 -0.0611 0.8038 0.0306
-6.500 -0.3576 0.03056 0.02586 -0.0597 0.7885 0.0317
-6.250 -0.3382 0.02892 0.02414 -0.0590 0.7751 0.0324
-6.000 -0.3184 0.02744 0.02248 -0.0582 0.7638 0.0335
-5.750 -0.2965 0.02656 0.02132 -0.0570 0.7539 0.0365
-5.500 -0.2819 0.01962 0.01342 -0.0535 0.7461 0.0261
-5.250 -0.2575 0.02044 0.01429 -0.0536 0.7373 0.0324
-5.000 -0.2315 0.01733 0.01058 -0.0516 0.7293 0.0247
-4.750 -0.2066 0.01603 0.00907 -0.0509 0.7217 0.0249
-4.500 -0.1821 0.01455 0.00756 -0.0504 0.7138 0.0259
-4.250 -0.1567 0.01392 0.00685 -0.0499 0.7071 0.0267
-4.000 -0.1311 0.01326 0.00614 -0.0493 0.7004 0.0273
-3.750 -0.1058 0.01272 0.00554 -0.0487 0.6941 0.0281
-3.500 -0.0805 0.01226 0.00501 -0.0481 0.6881 0.0290
-3.250 -0.0549 0.01185 0.00456 -0.0475 0.6819 0.0300
-3.000 -0.0302 0.01139 0.00402 -0.0468 0.6763 0.0315
-2.750 -0.0048 0.01100 0.00363 -0.0463 0.6707 0.0338
-2.500 0.0213 0.01073 0.00333 -0.0459 0.6649 0.0363
-2.000 0.0736 0.01020 0.00271 -0.0450 0.6535 0.0464
-1.750 0.0980 0.00966 0.00239 -0.0443 0.6479 0.1090
-1.500 0.1129 0.00815 0.00218 -0.0426 0.6429 0.4928
-1.250 0.1362 0.00780 0.00217 -0.0416 0.6368 0.5982
-1.000 0.1599 0.00757 0.00214 -0.0406 0.6312 0.6702
-0.750 0.1840 0.00740 0.00214 -0.0396 0.6257 0.7278
-0.500 0.2072 0.00717 0.00217 -0.0383 0.6196 0.8004
0.000 0.2676 0.00704 0.00230 -0.0383 0.6079 0.9265
0.250 0.3090 0.00711 0.00233 -0.0409 0.6012 0.9500
0.500 0.3497 0.00722 0.00236 -0.0435 0.5950 0.9635
0.750 0.3918 0.00729 0.00240 -0.0464 0.5877 0.9735
1.000 0.4316 0.00739 0.00240 -0.0489 0.5813 0.9801
1.250 0.4711 0.00741 0.00241 -0.0514 0.5736 0.9858
1.500 0.5112 0.00748 0.00238 -0.0541 0.5664 0.9909
1.750 0.5511 0.00749 0.00238 -0.0567 0.5571 0.9957
2.000 0.5919 0.00753 0.00236 -0.0596 0.5491 0.9999
2.250 0.6155 0.00756 0.00237 -0.0589 0.5412 1.0000
2.500 0.6385 0.00762 0.00239 -0.0579 0.5339 1.0000
2.750 0.6618 0.00768 0.00243 -0.0571 0.5254 1.0000
3.000 0.6851 0.00776 0.00248 -0.0562 0.5177 1.0000
3.250 0.7085 0.00785 0.00254 -0.0554 0.5085 1.0000
3.500 0.7321 0.00793 0.00261 -0.0545 0.4987 1.0000
3.750 0.7554 0.00806 0.00269 -0.0537 0.4898 1.0000
4.000 0.7791 0.00816 0.00278 -0.0529 0.4793 1.0000
4.250 0.8028 0.00828 0.00289 -0.0521 0.4693 1.0000
4.500 0.8262 0.00843 0.00301 -0.0512 0.4596 1.0000
4.750 0.8502 0.00855 0.00314 -0.0505 0.4502 1.0000
5.000 0.8740 0.00870 0.00328 -0.0498 0.4407 1.0000
5.250 0.8973 0.00887 0.00342 -0.0489 0.4298 1.0000
5.500 0.9208 0.00903 0.00358 -0.0481 0.4173 1.0000
5.750 0.9444 0.00920 0.00375 -0.0474 0.4059 1.0000
6.000 0.9676 0.00939 0.00393 -0.0466 0.3942 1.0000
6.250 0.9906 0.00962 0.00415 -0.0457 0.3838 1.0000
6.500 1.0133 0.00986 0.00437 -0.0448 0.3722 1.0000
6.750 1.0359 0.01010 0.00460 -0.0440 0.3578 1.0000
7.000 1.0579 0.01037 0.00485 -0.0430 0.3378 1.0000
7.250 1.0786 0.01073 0.00512 -0.0418 0.3126 1.0000
7.500 1.0988 0.01113 0.00544 -0.0406 0.2864 1.0000
7.750 1.1176 0.01163 0.00583 -0.0393 0.2572 1.0000
8.000 1.1344 0.01227 0.00631 -0.0376 0.2235 1.0000
8.250 1.1500 0.01299 0.00686 -0.0358 0.1911 1.0000
8.500 1.1655 0.01369 0.00744 -0.0341 0.1677 1.0000
9.000 1.1950 0.01512 0.00865 -0.0304 0.1177 1.0000
9.250 1.2073 0.01592 0.00933 -0.0282 0.0952 1.0000
9.500 1.2190 0.01670 0.01003 -0.0259 0.0808 1.0000
9.750 1.2305 0.01739 0.01070 -0.0236 0.0716 1.0000
10.000 1.2380 0.01812 0.01143 -0.0206 0.0640 1.0000
10.250 1.2447 0.01893 0.01224 -0.0176 0.0569 1.0000
10.500 1.2531 0.01974 0.01308 -0.0152 0.0502 1.0000
10.750 1.2574 0.02084 0.01418 -0.0125 0.0442 1.0000
11.000 1.2649 0.02186 0.01522 -0.0105 0.0394 1.0000
11.250 1.2682 0.02326 0.01664 -0.0084 0.0359 1.0000
11.500 1.2757 0.02449 0.01794 -0.0069 0.0334 1.0000
11.750 1.2794 0.02611 0.01958 -0.0055 0.0311 1.0000
12.000 1.2795 0.02815 0.02170 -0.0041 0.0295 1.0000
12.250 1.2862 0.02977 0.02341 -0.0033 0.0284 1.0000
12.500 1.2915 0.03156 0.02529 -0.0026 0.0272 1.0000
12.750 1.2952 0.03356 0.02736 -0.0020 0.0261 1.0000
13.000 1.2948 0.03600 0.02985 -0.0014 0.0251 1.0000
13.250 1.2899 0.03894 0.03286 -0.0008 0.0242 1.0000
13.500 1.2876 0.04167 0.03569 -0.0004 0.0236 1.0000
13.750 1.2928 0.04372 0.03784 -0.0002 0.0230 1.0000
14.000 1.2944 0.04617 0.04039 -0.0001 0.0223 1.0000
14.250 1.2941 0.04885 0.04316 0.0000 0.0218 1.0000
14.500 1.2951 0.05148 0.04587 -0.0001 0.0210 1.0000
14.750 1.2945 0.05437 0.04882 -0.0003 0.0206 1.0000
15.000 1.2915 0.05758 0.05210 -0.0006 0.0199 1.0000
15.250 1.2868 0.06104 0.05562 -0.0009 0.0195 1.0000
15.500 1.2808 0.06462 0.05928 -0.0011 0.0189 1.0000
15.750 1.2832 0.06753 0.06230 -0.0018 0.0185 1.0000
16.000 1.2829 0.07073 0.06562 -0.0024 0.0182 1.0000
16.250 1.2824 0.07401 0.06900 -0.0032 0.0179 1.0000
16.500 1.2816 0.07746 0.07255 -0.0042 0.0173 1.0000
16.750 1.2802 0.08098 0.07616 -0.0051 0.0169 1.0000
17.000 1.2787 0.08464 0.07990 -0.0063 0.0165 1.0000
17.250 1.2760 0.08847 0.08379 -0.0076 0.0160 1.0000
17.500 1.2741 0.09217 0.08757 -0.0088 0.0158 1.0000
17.750 1.2699 0.09608 0.09154 -0.0099 0.0154 1.0000
18.000 1.2643 0.10003 0.09558 -0.0106 0.0150 1.0000
18.250 1.2608 0.10435 0.10004 -0.0125 0.0149 1.0000
18.500 1.2559 0.10901 0.10484 -0.0146 0.0147 1.0000
18.750 1.2502 0.11390 0.10986 -0.0169 0.0144 1.0000
19.000 1.2445 0.11874 0.11484 -0.0192 0.0142 1.0000
19.250 1.2381 0.12378 0.12000 -0.0216 0.0140 1.0000
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Polar data table (+)
Polar graphs
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