BOEING-VERTOL VR-5 AIRFOIL (vr5-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-5 AIRFOIL (vr5-il) Reynolds number: 200,000 Max Cl/Cd: 79.93 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-vr5-il-200000.txt Download as CSV file: xf-vr5-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: BOEING-VERTOL VR-5 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4219 0.10501 0.10196 -0.0189 1.0000 0.0410
-9.500 -0.4200 0.10011 0.09710 -0.0273 1.0000 0.0415
-9.250 -0.4171 0.09441 0.09145 -0.0365 1.0000 0.0417
-9.000 -0.4130 0.08828 0.08525 -0.0470 0.9643 0.0418
-8.750 -0.4085 0.08298 0.08002 -0.0442 0.9508 0.0426
-8.500 -0.4022 0.08123 0.07825 -0.0399 0.9356 0.0434
-8.250 -0.4031 0.07811 0.07511 -0.0405 0.9194 0.0440
-8.000 -0.4040 0.07449 0.07142 -0.0429 0.9054 0.0446
-7.750 -0.4013 0.07081 0.06766 -0.0450 0.8934 0.0456
-7.500 -0.3974 0.06696 0.06370 -0.0473 0.8828 0.0469
-7.250 -0.3917 0.06298 0.05956 -0.0496 0.8729 0.0486
-7.000 -0.3802 0.06010 0.05600 -0.0541 0.8618 0.0525
-6.750 -0.3742 0.05363 0.04939 -0.0550 0.8543 0.0536
-6.500 -0.3596 0.05026 0.04606 -0.0549 0.8458 0.0549
-6.250 -0.3432 0.04787 0.04362 -0.0548 0.8380 0.0573
-6.000 -0.3187 0.04880 0.04373 -0.0546 0.8296 0.0652
-5.750 -0.3064 0.04177 0.03687 -0.0557 0.8227 0.0678
-5.500 -0.2863 0.03946 0.03449 -0.0556 0.8151 0.0709
-5.250 -0.2636 0.03737 0.03182 -0.0556 0.8079 0.0806
-5.000 -0.2423 0.03463 0.02913 -0.0556 0.8004 0.0838
-4.750 -0.2187 0.03296 0.02703 -0.0554 0.7937 0.0957
-4.500 -0.1950 0.03072 0.02479 -0.0555 0.7862 0.1013
-4.250 -0.1591 0.02399 0.01650 -0.0525 0.7820 0.0535
-4.000 -0.1307 0.02248 0.01472 -0.0523 0.7745 0.0530
-3.750 -0.1051 0.02017 0.01226 -0.0520 0.7687 0.0557
-3.500 -0.0777 0.01914 0.01113 -0.0518 0.7622 0.0585
-3.250 -0.0502 0.01815 0.00998 -0.0514 0.7556 0.0609
-3.000 -0.0229 0.01756 0.00920 -0.0509 0.7505 0.0643
-2.750 0.0047 0.01654 0.00815 -0.0508 0.7437 0.0664
-2.500 0.0309 0.01578 0.00740 -0.0505 0.7386 0.0711
-2.250 0.0581 0.01528 0.00687 -0.0504 0.7330 0.0749
-2.000 0.0857 0.01488 0.00641 -0.0503 0.7269 0.0786
-1.750 0.1122 0.01433 0.00588 -0.0501 0.7224 0.0867
-1.500 0.1402 0.01399 0.00554 -0.0503 0.7169 0.0983
-1.250 0.1649 0.01253 0.00506 -0.0506 0.7115 0.3640
-1.000 0.1773 0.01140 0.00539 -0.0466 0.7074 0.7809
-0.750 0.1987 0.01146 0.00553 -0.0445 0.7026 0.8352
-0.500 0.2203 0.01153 0.00564 -0.0425 0.6971 0.8687
-0.250 0.2393 0.01160 0.00568 -0.0396 0.6929 0.9051
0.000 0.2605 0.01165 0.00569 -0.0373 0.6889 0.9418
0.250 0.3057 0.01172 0.00573 -0.0400 0.6834 0.9727
0.500 0.3559 0.01176 0.00566 -0.0446 0.6789 0.9853
0.750 0.3997 0.01180 0.00557 -0.0481 0.6754 0.9935
1.000 0.4400 0.01189 0.00564 -0.0513 0.6703 1.0000
1.250 0.4624 0.01198 0.00569 -0.0511 0.6655 1.0000
1.500 0.4846 0.01207 0.00572 -0.0505 0.6617 1.0000
1.750 0.5077 0.01221 0.00581 -0.0501 0.6574 1.0000
2.000 0.5323 0.01234 0.00593 -0.0499 0.6511 1.0000
2.250 0.5583 0.01239 0.00589 -0.0497 0.6460 1.0000
2.500 0.5853 0.01255 0.00603 -0.0499 0.6403 1.0000
2.750 0.6128 0.01268 0.00616 -0.0501 0.6347 1.0000
3.000 0.6405 0.01277 0.00619 -0.0501 0.6303 1.0000
3.250 0.6682 0.01294 0.00639 -0.0504 0.6242 1.0000
3.500 0.6960 0.01304 0.00649 -0.0505 0.6183 1.0000
3.750 0.7241 0.01313 0.00652 -0.0505 0.6141 1.0000
4.000 0.7518 0.01336 0.00686 -0.0509 0.6079 1.0000
4.250 0.7797 0.01349 0.00701 -0.0511 0.6028 1.0000
4.500 0.8080 0.01361 0.00709 -0.0511 0.5987 1.0000
4.750 0.8353 0.01383 0.00745 -0.0514 0.5913 1.0000
5.000 0.8634 0.01385 0.00745 -0.0514 0.5853 1.0000
5.250 0.8906 0.01397 0.00766 -0.0514 0.5768 1.0000
5.500 0.9187 0.01394 0.00760 -0.0513 0.5694 1.0000
5.750 0.9455 0.01398 0.00774 -0.0512 0.5585 1.0000
6.000 0.9726 0.01399 0.00780 -0.0511 0.5479 1.0000
6.250 0.9999 0.01397 0.00777 -0.0509 0.5372 1.0000
6.500 1.0264 0.01392 0.00777 -0.0506 0.5228 1.0000
6.750 1.0523 0.01390 0.00784 -0.0504 0.5058 1.0000
7.000 1.0782 0.01392 0.00797 -0.0502 0.4874 1.0000
7.250 1.1039 0.01398 0.00812 -0.0499 0.4672 1.0000
7.500 1.1286 0.01412 0.00829 -0.0496 0.4392 1.0000
7.750 1.1505 0.01449 0.00851 -0.0490 0.3942 1.0000
8.000 1.1678 0.01538 0.00910 -0.0480 0.3339 1.0000
8.250 1.1801 0.01677 0.01011 -0.0467 0.2691 1.0000
8.500 1.1890 0.01844 0.01142 -0.0452 0.2021 1.0000
8.750 1.1881 0.02083 0.01323 -0.0430 0.1245 1.0000
9.000 1.1894 0.02280 0.01500 -0.0409 0.0941 1.0000
9.250 1.1913 0.02472 0.01682 -0.0390 0.0771 1.0000
9.500 1.1918 0.02686 0.01891 -0.0374 0.0664 1.0000
9.750 1.1952 0.02887 0.02095 -0.0361 0.0584 1.0000
10.000 1.1969 0.03108 0.02323 -0.0347 0.0529 1.0000
10.250 1.2018 0.03307 0.02525 -0.0336 0.0485 1.0000
10.500 1.2006 0.03561 0.02775 -0.0319 0.0455 1.0000
10.750 1.2100 0.03727 0.02954 -0.0309 0.0429 1.0000
11.000 1.2182 0.03902 0.03135 -0.0300 0.0404 1.0000
11.250 1.2255 0.04086 0.03319 -0.0290 0.0383 1.0000
11.500 1.2352 0.04267 0.03497 -0.0269 0.0364 1.0000
11.750 1.2480 0.04419 0.03663 -0.0258 0.0354 1.0000
12.000 1.2616 0.04575 0.03833 -0.0245 0.0343 1.0000
12.250 1.2758 0.04738 0.04007 -0.0233 0.0332 1.0000
12.500 1.2886 0.04918 0.04200 -0.0222 0.0323 1.0000
12.750 1.2993 0.05109 0.04401 -0.0213 0.0313 1.0000
13.000 1.3110 0.05305 0.04602 -0.0204 0.0302 1.0000
13.250 1.3319 0.05633 0.04944 -0.0188 0.0291 1.0000
13.500 1.3320 0.05918 0.05254 -0.0180 0.0289 1.0000
13.750 1.3298 0.06238 0.05601 -0.0174 0.0287 1.0000
14.000 1.3250 0.06596 0.05984 -0.0168 0.0286 1.0000
14.250 1.3172 0.06991 0.06406 -0.0166 0.0285 1.0000
14.500 1.3065 0.07423 0.06864 -0.0166 0.0284 1.0000
14.750 1.2931 0.07895 0.07361 -0.0170 0.0284 1.0000
15.000 1.2774 0.08403 0.07892 -0.0178 0.0285 1.0000
15.250 1.2599 0.08950 0.08462 -0.0191 0.0285 1.0000
15.500 1.2409 0.09543 0.09077 -0.0209 0.0286 1.0000
15.750 1.2212 0.10184 0.09738 -0.0233 0.0287 1.0000
16.000 1.2007 0.10879 0.10452 -0.0263 0.0288 1.0000
16.250 1.1805 0.11623 0.11213 -0.0296 0.0290 1.0000
16.500 1.1632 0.12336 0.11943 -0.0334 0.0292 1.0000
16.750 1.1447 0.13109 0.12735 -0.0387 0.0294 1.0000
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Polar data table (+)
Polar graphs
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