BOEING-VERTOL VR-11X AIRFOIL (vr11x-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-11X AIRFOIL (vr11x-il) Reynolds number: 50,000 Max Cl/Cd: 29.35 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-vr11x-il-50000-n5.txt Download as CSV file: xf-vr11x-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BOEING-VERTOL VR-11X 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.5357 0.08153 0.07503 -0.0265 1.0000 0.0706
-7.000 -0.5596 0.07657 0.06965 -0.0255 1.0000 0.0608
-6.750 -0.5499 0.07333 0.06651 -0.0237 1.0000 0.0588
-6.500 -0.5490 0.07005 0.06317 -0.0218 1.0000 0.0570
-6.250 -0.5487 0.06652 0.05948 -0.0200 1.0000 0.0549
-5.750 -0.5440 0.05874 0.05077 -0.0158 1.0000 0.0487
-5.500 -0.5351 0.05568 0.04757 -0.0141 1.0000 0.0480
-5.250 -0.5251 0.05273 0.04438 -0.0122 1.0000 0.0473
-5.000 -0.5133 0.04986 0.04123 -0.0104 1.0000 0.0466
-4.750 -0.4998 0.04713 0.03816 -0.0086 1.0000 0.0460
-4.500 -0.4843 0.04454 0.03519 -0.0068 1.0000 0.0454
-4.250 -0.4669 0.04213 0.03238 -0.0052 1.0000 0.0451
-4.000 -0.4477 0.03993 0.02978 -0.0036 1.0000 0.0450
-3.750 -0.4269 0.03803 0.02749 -0.0023 1.0000 0.0458
-3.500 -0.4048 0.03637 0.02541 -0.0010 1.0000 0.0473
-3.250 -0.3814 0.03490 0.02352 0.0002 1.0000 0.0486
-3.000 -0.3573 0.03350 0.02180 0.0012 1.0000 0.0494
-2.750 -0.3326 0.03199 0.02016 0.0019 1.0000 0.0504
-2.500 -0.3076 0.03078 0.01885 0.0025 1.0000 0.0518
-2.250 -0.2825 0.02983 0.01781 0.0032 1.0000 0.0542
-2.000 -0.2569 0.02909 0.01690 0.0039 1.0000 0.0584
-1.750 -0.2235 0.02831 0.01601 0.0028 0.9976 0.0631
-1.500 -0.1887 0.02775 0.01531 0.0014 0.9940 0.0695
-1.250 -0.1558 0.02722 0.01469 0.0002 0.9898 0.0815
-1.000 -0.0661 0.02352 0.01466 -0.0111 0.9957 1.0000
-0.750 -0.0326 0.02385 0.01448 -0.0125 0.9900 1.0000
-0.500 0.0027 0.02426 0.01451 -0.0145 0.9841 1.0000
-0.250 0.0396 0.02469 0.01465 -0.0168 0.9768 1.0000
0.000 0.0784 0.02516 0.01486 -0.0195 0.9683 1.0000
0.250 0.1185 0.02559 0.01510 -0.0223 0.9577 1.0000
0.500 0.1605 0.02593 0.01528 -0.0254 0.9437 1.0000
0.750 0.2066 0.02620 0.01542 -0.0290 0.9284 1.0000
1.000 0.2576 0.02632 0.01545 -0.0333 0.9112 1.0000
1.250 0.3160 0.02614 0.01520 -0.0385 0.8908 1.0000
1.500 0.3668 0.02568 0.01470 -0.0418 0.8673 1.0000
1.750 0.4074 0.02523 0.01424 -0.0431 0.8472 1.0000
2.000 0.4326 0.02499 0.01401 -0.0419 0.8275 1.0000
2.250 0.4590 0.02463 0.01368 -0.0408 0.8070 1.0000
2.750 0.4681 0.02460 0.01372 -0.0317 0.7409 1.0000
3.000 0.4798 0.02440 0.01354 -0.0282 0.6989 1.0000
3.250 0.5278 0.02312 0.01221 -0.0294 0.6504 1.0000
3.500 0.5902 0.02175 0.01033 -0.0322 0.5638 1.0000
3.750 0.6163 0.02209 0.01012 -0.0309 0.4845 1.0000
4.000 0.6335 0.02281 0.01040 -0.0287 0.4270 1.0000
4.250 0.6502 0.02359 0.01080 -0.0267 0.3867 1.0000
4.500 0.6687 0.02432 0.01127 -0.0251 0.3575 1.0000
4.750 0.6892 0.02503 0.01177 -0.0239 0.3372 1.0000
5.000 0.7114 0.02572 0.01233 -0.0229 0.3207 1.0000
5.250 0.7352 0.02638 0.01289 -0.0223 0.3067 1.0000
5.500 0.7601 0.02702 0.01351 -0.0218 0.2941 1.0000
5.750 0.7862 0.02767 0.01413 -0.0216 0.2839 1.0000
6.000 0.8138 0.02833 0.01482 -0.0216 0.2753 1.0000
6.250 0.8416 0.02902 0.01556 -0.0216 0.2675 1.0000
6.500 0.8678 0.02973 0.01630 -0.0214 0.2599 1.0000
6.750 0.8937 0.03049 0.01715 -0.0212 0.2530 1.0000
7.000 0.9187 0.03130 0.01807 -0.0209 0.2466 1.0000
7.500 0.9670 0.03310 0.02007 -0.0200 0.2349 1.0000
7.750 0.9900 0.03402 0.02109 -0.0194 0.2291 1.0000
8.000 1.0133 0.03504 0.02219 -0.0189 0.2240 1.0000
8.250 1.0329 0.03617 0.02359 -0.0179 0.2181 1.0000
8.500 1.0545 0.03717 0.02467 -0.0172 0.2125 1.0000
8.750 1.0736 0.03841 0.02609 -0.0162 0.2072 1.0000
9.000 1.0903 0.03971 0.02767 -0.0149 0.2014 1.0000
9.250 1.1111 0.04078 0.02878 -0.0142 0.1962 1.0000
9.500 1.1253 0.04232 0.03062 -0.0127 0.1911 1.0000
9.750 1.1378 0.04388 0.03248 -0.0110 0.1856 1.0000
10.000 1.1565 0.04508 0.03376 -0.0100 0.1808 1.0000
10.250 1.1681 0.04688 0.03581 -0.0083 0.1765 1.0000
10.500 1.1719 0.04909 0.03845 -0.0058 0.1720 1.0000
10.750 1.1809 0.05086 0.04045 -0.0039 0.1676 1.0000
11.000 1.2019 0.05201 0.04158 -0.0034 0.1633 1.0000
11.250 1.1906 0.05492 0.04496 0.0004 0.1596 1.0000
11.500 1.1794 0.05783 0.04823 0.0038 0.1561 1.0000
11.750 1.1712 0.06053 0.05117 0.0068 0.1532 1.0000
12.000 1.1703 0.06268 0.05347 0.0092 0.1502 1.0000
12.250 1.1807 0.06435 0.05520 0.0105 0.1469 1.0000
12.500 1.1392 0.06921 0.06036 0.0144 0.1458 1.0000
12.750 1.0889 0.07596 0.06731 0.0161 0.1452 1.0000
13.000 1.0153 0.08755 0.07902 0.0133 0.1453 1.0000
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Polar data table (+)
Polar graphs
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