BOEING-VERTOL VR-12 AIRFOIL (vr12-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-12 AIRFOIL (vr12-il) Reynolds number: 50,000 Max Cl/Cd: 28.88 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-vr12-il-50000.txt Download as CSV file: xf-vr12-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: BOEING-VERTOL VR-12 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4475 0.10340 0.09697 -0.0007 1.0000 0.2850
-8.250 -0.4477 0.10044 0.09409 -0.0006 1.0000 0.3016
-8.000 -0.4526 0.09781 0.09155 -0.0006 1.0000 0.3185
-7.750 -0.4246 0.09300 0.08671 0.0018 1.0000 0.3412
-7.500 -0.4326 0.09093 0.08475 0.0027 1.0000 0.3652
-7.250 -0.4223 0.08789 0.08176 0.0051 1.0000 0.3966
-7.000 -0.3957 0.08399 0.07786 0.0082 1.0000 0.4358
-6.750 -0.3874 0.08146 0.07539 0.0111 1.0000 0.4745
-6.500 -0.3637 0.07792 0.07184 0.0136 1.0000 0.5163
-6.250 -0.3489 0.07553 0.06948 0.0174 1.0000 0.5707
-4.750 -0.4895 0.04971 0.04236 -0.0066 1.0000 0.2090
-4.500 -0.4697 0.04513 0.03721 -0.0059 1.0000 0.1737
-4.250 -0.4523 0.04194 0.03340 -0.0043 1.0000 0.1587
-4.000 -0.4348 0.03931 0.03045 -0.0028 1.0000 0.1555
-3.750 -0.4152 0.03688 0.02754 -0.0013 1.0000 0.1511
-3.500 -0.3926 0.03521 0.02506 0.0005 1.0000 0.1456
-3.250 -0.3700 0.03339 0.02288 0.0016 1.0000 0.1457
-3.000 -0.3468 0.03144 0.02088 0.0023 1.0000 0.1492
-2.750 -0.3217 0.03003 0.01925 0.0030 1.0000 0.1513
-2.500 -0.2953 0.02881 0.01782 0.0037 1.0000 0.1539
-2.250 -0.2689 0.02792 0.01666 0.0043 1.0000 0.1604
-2.000 -0.2397 0.02686 0.01566 0.0043 1.0000 0.1693
-1.750 -0.2097 0.02609 0.01479 0.0043 1.0000 0.1792
-1.500 -0.0814 0.02147 0.01355 -0.0109 1.0000 1.0000
-1.250 -0.0684 0.02169 0.01321 -0.0084 1.0000 1.0000
-1.000 -0.0559 0.02192 0.01310 -0.0063 1.0000 1.0000
-0.750 -0.0431 0.02218 0.01310 -0.0043 1.0000 1.0000
-0.500 -0.0299 0.02248 0.01316 -0.0024 1.0000 1.0000
-0.250 -0.0161 0.02282 0.01331 -0.0008 1.0000 1.0000
0.000 -0.0020 0.02320 0.01352 0.0007 1.0000 1.0000
0.250 0.0125 0.02363 0.01381 0.0021 1.0000 1.0000
0.500 0.0271 0.02412 0.01416 0.0032 1.0000 1.0000
0.750 0.0419 0.02466 0.01460 0.0043 1.0000 1.0000
1.000 0.0919 0.02569 0.01551 -0.0015 0.9870 1.0000
1.250 0.1734 0.02692 0.01664 -0.0127 0.9598 1.0000
1.500 0.2513 0.02770 0.01740 -0.0224 0.9307 1.0000
1.750 0.3314 0.02790 0.01767 -0.0315 0.8996 1.0000
2.000 0.4069 0.02748 0.01738 -0.0388 0.8649 1.0000
2.250 0.4703 0.02647 0.01651 -0.0425 0.8278 1.0000
2.500 0.5225 0.02497 0.01511 -0.0428 0.7889 1.0000
2.750 0.5563 0.02352 0.01368 -0.0396 0.7423 1.0000
3.000 0.5800 0.02241 0.01244 -0.0351 0.6836 1.0000
3.250 0.6018 0.02174 0.01142 -0.0308 0.6200 1.0000
3.500 0.6229 0.02183 0.01107 -0.0278 0.5627 1.0000
3.750 0.6451 0.02239 0.01125 -0.0258 0.5189 1.0000
4.000 0.6680 0.02313 0.01167 -0.0243 0.4855 1.0000
4.250 0.6914 0.02403 0.01235 -0.0232 0.4590 1.0000
4.500 0.7153 0.02495 0.01309 -0.0222 0.4371 1.0000
4.750 0.7393 0.02594 0.01392 -0.0214 0.4187 1.0000
5.000 0.7630 0.02699 0.01492 -0.0206 0.4031 1.0000
5.250 0.7864 0.02808 0.01600 -0.0199 0.3891 1.0000
5.500 0.8085 0.02925 0.01726 -0.0191 0.3760 1.0000
5.750 0.8303 0.03055 0.01865 -0.0183 0.3647 1.0000
6.000 0.8539 0.03190 0.01998 -0.0176 0.3561 1.0000
6.250 0.8736 0.03348 0.02180 -0.0168 0.3475 1.0000
6.500 0.8953 0.03502 0.02341 -0.0160 0.3399 1.0000
6.750 0.9124 0.03677 0.02542 -0.0150 0.3317 1.0000
7.000 0.9336 0.03843 0.02710 -0.0142 0.3249 1.0000
7.250 0.9449 0.04086 0.02995 -0.0129 0.3196 1.0000
7.500 0.9602 0.04308 0.03240 -0.0119 0.3146 1.0000
7.750 0.9789 0.04519 0.03457 -0.0110 0.3095 1.0000
8.000 0.9777 0.04860 0.03845 -0.0092 0.3049 1.0000
8.250 0.9831 0.05158 0.04168 -0.0077 0.3001 1.0000
8.500 1.0038 0.05373 0.04385 -0.0070 0.2954 1.0000
8.750 0.9898 0.05852 0.04899 -0.0052 0.2934 1.0000
9.000 0.9620 0.06454 0.05528 -0.0036 0.2928 1.0000
9.250 0.9265 0.07158 0.06246 -0.0030 0.2936 1.0000
9.500 0.8946 0.07873 0.06966 -0.0033 0.2951 1.0000
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Polar data table (+)
Polar graphs
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