BOEING-VERTOL VR-13 AIRFOIL (vr13-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-13 AIRFOIL (vr13-il) Reynolds number: 200,000 Max Cl/Cd: 54.18 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-vr13-il-200000-n5.txt Download as CSV file: xf-vr13-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BOEING-VERTOL VR-13 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5298 0.08949 0.08610 -0.0072 1.0000 0.0116
-8.750 -0.5326 0.08410 0.08075 -0.0113 1.0000 0.0116
-8.500 -0.5380 0.07816 0.07484 -0.0173 1.0000 0.0116
-8.250 -0.5442 0.07244 0.06910 -0.0216 1.0000 0.0115
-8.000 -0.5488 0.06562 0.06218 -0.0257 1.0000 0.0117
-7.750 -0.5543 0.05776 0.05412 -0.0283 1.0000 0.0120
-7.500 -0.5521 0.05253 0.04870 -0.0287 1.0000 0.0124
-7.250 -0.5381 0.05154 0.04767 -0.0284 1.0000 0.0129
-7.000 -0.5327 0.04827 0.04425 -0.0271 1.0000 0.0134
-6.500 -0.5058 0.03611 0.03117 -0.0274 0.9849 0.0144
-6.250 -0.4932 0.02717 0.02100 -0.0255 0.9761 0.0159
-6.000 -0.4647 0.02652 0.02028 -0.0263 0.9706 0.0167
-5.750 -0.4362 0.02546 0.01900 -0.0269 0.9651 0.0186
-5.500 -0.4110 0.02294 0.01591 -0.0262 0.9585 0.0209
-5.250 -0.3839 0.02238 0.01530 -0.0264 0.9522 0.0224
-5.000 -0.3577 0.02133 0.01400 -0.0260 0.9458 0.0247
-4.750 -0.3313 0.02000 0.01229 -0.0253 0.9391 0.0261
-4.500 -0.3058 0.01880 0.01101 -0.0249 0.9329 0.0275
-4.250 -0.2804 0.01828 0.01044 -0.0244 0.9258 0.0296
-4.000 -0.2544 0.01755 0.00959 -0.0237 0.9201 0.0315
-3.750 -0.2289 0.01686 0.00879 -0.0230 0.9126 0.0330
-3.500 -0.2041 0.01607 0.00793 -0.0222 0.9069 0.0350
-3.250 -0.1795 0.01541 0.00728 -0.0215 0.8996 0.0368
-3.000 -0.1549 0.01488 0.00672 -0.0206 0.8935 0.0384
-2.750 -0.1299 0.01443 0.00624 -0.0198 0.8873 0.0405
-2.500 -0.1047 0.01408 0.00584 -0.0191 0.8806 0.0431
-2.250 -0.0810 0.01362 0.00534 -0.0180 0.8726 0.0451
-2.000 -0.0580 0.01319 0.00486 -0.0166 0.8621 0.0478
-1.750 -0.0341 0.01287 0.00450 -0.0154 0.8488 0.0522
-1.500 -0.0097 0.01259 0.00414 -0.0143 0.8353 0.0572
-1.250 0.0149 0.01226 0.00382 -0.0133 0.8223 0.0679
-1.000 0.0383 0.01173 0.00354 -0.0122 0.8097 0.1371
-0.750 0.0529 0.01023 0.00327 -0.0099 0.7975 0.4802
-0.500 0.1416 0.00945 0.00395 -0.0205 0.7835 0.9761
-0.250 0.2055 0.00958 0.00390 -0.0278 0.7686 1.0000
0.000 0.2309 0.00954 0.00374 -0.0272 0.7534 1.0000
0.250 0.2565 0.00952 0.00360 -0.0267 0.7363 1.0000
0.500 0.2822 0.00951 0.00348 -0.0261 0.7165 1.0000
0.750 0.3078 0.00952 0.00336 -0.0255 0.6919 1.0000
1.000 0.3332 0.00956 0.00324 -0.0249 0.6591 1.0000
1.250 0.3584 0.00966 0.00311 -0.0242 0.6107 1.0000
1.500 0.3830 0.00995 0.00301 -0.0235 0.5363 1.0000
1.750 0.4073 0.01043 0.00302 -0.0230 0.4527 1.0000
2.000 0.4318 0.01090 0.00313 -0.0227 0.3846 1.0000
2.250 0.4564 0.01131 0.00326 -0.0223 0.3389 1.0000
2.500 0.4810 0.01164 0.00340 -0.0219 0.3094 1.0000
2.750 0.5057 0.01193 0.00355 -0.0215 0.2878 1.0000
3.000 0.5303 0.01219 0.00372 -0.0210 0.2706 1.0000
3.250 0.5548 0.01245 0.00389 -0.0205 0.2570 1.0000
3.500 0.5792 0.01272 0.00407 -0.0199 0.2456 1.0000
3.750 0.6036 0.01296 0.00427 -0.0194 0.2353 1.0000
4.000 0.6279 0.01322 0.00449 -0.0188 0.2265 1.0000
4.250 0.6520 0.01349 0.00472 -0.0182 0.2181 1.0000
4.500 0.6762 0.01375 0.00496 -0.0176 0.2103 1.0000
4.750 0.6999 0.01405 0.00522 -0.0170 0.2027 1.0000
5.000 0.7239 0.01431 0.00549 -0.0163 0.1956 1.0000
5.250 0.7476 0.01462 0.00577 -0.0157 0.1893 1.0000
5.500 0.7711 0.01493 0.00610 -0.0150 0.1840 1.0000
5.750 0.7948 0.01523 0.00643 -0.0143 0.1785 1.0000
6.000 0.8178 0.01559 0.00675 -0.0136 0.1733 1.0000
6.250 0.8412 0.01590 0.00711 -0.0128 0.1679 1.0000
6.500 0.8645 0.01623 0.00746 -0.0121 0.1623 1.0000
6.750 0.8869 0.01662 0.00783 -0.0113 0.1573 1.0000
7.000 0.9102 0.01694 0.00823 -0.0106 0.1526 1.0000
7.250 0.9330 0.01730 0.00863 -0.0099 0.1480 1.0000
7.500 0.9548 0.01775 0.00906 -0.0090 0.1437 1.0000
7.750 0.9777 0.01808 0.00951 -0.0082 0.1393 1.0000
8.000 1.0001 0.01846 0.00995 -0.0074 0.1348 1.0000
8.250 1.0214 0.01892 0.01042 -0.0065 0.1310 1.0000
8.500 1.0433 0.01935 0.01096 -0.0057 0.1274 1.0000
8.750 1.0652 0.01974 0.01146 -0.0048 0.1227 1.0000
9.000 1.0859 0.02019 0.01192 -0.0039 0.1178 1.0000
9.250 1.1073 0.02061 0.01245 -0.0030 0.1123 1.0000
9.500 1.1280 0.02103 0.01296 -0.0021 0.1064 1.0000
9.750 1.1479 0.02154 0.01354 -0.0011 0.1013 1.0000
10.000 1.1683 0.02201 0.01413 -0.0001 0.0952 1.0000
10.250 1.1868 0.02260 0.01474 0.0010 0.0898 1.0000
10.500 1.2065 0.02313 0.01543 0.0020 0.0832 1.0000
10.750 1.2240 0.02379 0.01613 0.0032 0.0772 1.0000
11.000 1.2416 0.02445 0.01689 0.0044 0.0710 1.0000
11.250 1.2569 0.02526 0.01774 0.0058 0.0659 1.0000
11.500 1.2717 0.02609 0.01867 0.0072 0.0609 1.0000
12.000 1.2935 0.02808 0.02084 0.0110 0.0532 1.0000
12.250 1.3010 0.02920 0.02205 0.0132 0.0501 1.0000
12.500 1.3052 0.03058 0.02350 0.0154 0.0476 1.0000
12.750 1.3099 0.03203 0.02507 0.0173 0.0454 1.0000
13.000 1.3163 0.03346 0.02668 0.0189 0.0432 1.0000
13.250 1.3207 0.03510 0.02847 0.0203 0.0411 1.0000
13.500 1.3223 0.03704 0.03053 0.0215 0.0393 1.0000
13.750 1.3201 0.03943 0.03302 0.0225 0.0378 1.0000
14.000 1.3171 0.04207 0.03579 0.0232 0.0366 1.0000
14.250 1.3165 0.04467 0.03858 0.0234 0.0355 1.0000
14.500 1.3132 0.04771 0.04182 0.0233 0.0345 1.0000
14.750 1.3074 0.05122 0.04551 0.0228 0.0336 1.0000
15.000 1.2995 0.05528 0.04973 0.0216 0.0328 1.0000
15.250 1.2890 0.05998 0.05460 0.0198 0.0322 1.0000
15.500 1.2760 0.06543 0.06021 0.0172 0.0317 1.0000
15.750 1.2601 0.07170 0.06664 0.0140 0.0313 1.0000
16.000 1.2420 0.07865 0.07376 0.0103 0.0310 1.0000
16.250 1.2222 0.08611 0.08136 0.0064 0.0308 1.0000
16.500 1.2017 0.09378 0.08916 0.0024 0.0306 1.0000
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Polar data table (+)
Polar graphs
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