BOEING-VERTOL VR-11X AIRFOIL (vr11x-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-11X AIRFOIL (vr11x-il) Reynolds number: 200,000 Max Cl/Cd: 51.57 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-vr11x-il-200000-n5.txt Download as CSV file: xf-vr11x-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3903 0.08742 0.08386 -0.0461 0.9341 0.0290
-8.750 -0.3897 0.08276 0.07922 -0.0501 0.9319 0.0293
-8.500 -0.3922 0.07737 0.07383 -0.0560 0.9291 0.0295
-8.250 -0.3978 0.07239 0.06880 -0.0602 0.9265 0.0297
-8.000 -0.4021 0.06813 0.06444 -0.0621 0.9244 0.0300
-7.500 -0.4077 0.05877 0.05443 -0.0646 0.9202 0.0322
-7.000 -0.4056 0.04419 0.03913 -0.0617 0.9163 0.0171
-6.750 -0.3926 0.04187 0.03670 -0.0608 0.9147 0.0169
-6.500 -0.3796 0.03940 0.03402 -0.0596 0.9131 0.0167
-6.250 -0.3658 0.03680 0.03115 -0.0581 0.9118 0.0164
-6.000 -0.3509 0.03417 0.02822 -0.0565 0.9106 0.0162
-5.750 -0.3345 0.03168 0.02538 -0.0547 0.9095 0.0160
-5.500 -0.3164 0.02933 0.02267 -0.0530 0.9085 0.0158
-5.250 -0.2964 0.02724 0.02022 -0.0515 0.9077 0.0159
-5.000 -0.2746 0.02547 0.01810 -0.0502 0.9068 0.0160
-4.750 -0.2517 0.02396 0.01629 -0.0492 0.9055 0.0162
-4.500 -0.2280 0.02271 0.01478 -0.0483 0.9040 0.0166
-4.250 -0.2040 0.02176 0.01364 -0.0476 0.9027 0.0176
-4.000 -0.1802 0.02115 0.01300 -0.0471 0.9013 0.0186
-3.750 -0.1556 0.02040 0.01217 -0.0464 0.8997 0.0192
-3.500 -0.1309 0.01961 0.01131 -0.0457 0.8980 0.0197
-3.250 -0.1064 0.01893 0.01056 -0.0449 0.8965 0.0202
-3.000 -0.0818 0.01832 0.00990 -0.0440 0.8948 0.0209
-2.750 -0.0575 0.01773 0.00929 -0.0431 0.8931 0.0217
-2.500 -0.0371 0.01734 0.00892 -0.0417 0.8890 0.0228
-2.250 -0.0139 0.01695 0.00851 -0.0406 0.8841 0.0248
-2.000 0.0121 0.01641 0.00794 -0.0396 0.8797 0.0281
-1.750 0.0351 0.01606 0.00756 -0.0383 0.8738 0.0315
-1.500 0.0594 0.01557 0.00704 -0.0369 0.8676 0.0380
-1.250 0.0825 0.01493 0.00651 -0.0353 0.8613 0.0688
-1.000 0.0887 0.01291 0.00610 -0.0312 0.8534 0.4845
-0.750 0.2121 0.01180 0.00644 -0.0480 0.8456 0.9722
-0.500 0.2517 0.01167 0.00617 -0.0499 0.8374 0.9844
-0.250 0.2888 0.01157 0.00598 -0.0518 0.8286 0.9903
0.250 0.3611 0.01128 0.00556 -0.0553 0.8103 1.0000
0.500 0.3859 0.01117 0.00542 -0.0548 0.7965 1.0000
1.000 0.4350 0.01095 0.00514 -0.0536 0.7388 1.0000
1.250 0.4488 0.01035 0.00387 -0.0489 0.6310 1.0000
1.500 0.4704 0.01084 0.00379 -0.0476 0.5442 1.0000
1.750 0.4931 0.01136 0.00391 -0.0469 0.4689 1.0000
2.000 0.5152 0.01190 0.00407 -0.0461 0.4035 1.0000
2.250 0.5371 0.01238 0.00424 -0.0454 0.3496 1.0000
2.500 0.5591 0.01280 0.00441 -0.0446 0.3123 1.0000
2.750 0.5814 0.01316 0.00460 -0.0437 0.2837 1.0000
3.000 0.6036 0.01349 0.00477 -0.0429 0.2592 1.0000
3.250 0.6258 0.01380 0.00495 -0.0420 0.2410 1.0000
3.500 0.6481 0.01410 0.00515 -0.0411 0.2280 1.0000
3.750 0.6704 0.01438 0.00537 -0.0402 0.2187 1.0000
4.000 0.6922 0.01470 0.00561 -0.0393 0.2114 1.0000
4.250 0.7144 0.01498 0.00585 -0.0383 0.2054 1.0000
4.500 0.7363 0.01528 0.00611 -0.0374 0.1998 1.0000
4.750 0.7575 0.01564 0.00642 -0.0363 0.1951 1.0000
5.000 0.7795 0.01592 0.00670 -0.0353 0.1915 1.0000
5.250 0.8014 0.01622 0.00701 -0.0343 0.1881 1.0000
5.500 0.8230 0.01655 0.00733 -0.0333 0.1848 1.0000
5.750 0.8440 0.01692 0.00769 -0.0322 0.1816 1.0000
6.000 0.8648 0.01734 0.00807 -0.0311 0.1784 1.0000
6.250 0.8868 0.01764 0.00842 -0.0301 0.1756 1.0000
6.500 0.9084 0.01797 0.00880 -0.0291 0.1726 1.0000
6.750 0.9296 0.01831 0.00916 -0.0281 0.1687 1.0000
7.000 0.9500 0.01872 0.00954 -0.0269 0.1647 1.0000
7.250 0.9709 0.01911 0.00995 -0.0259 0.1611 1.0000
7.500 0.9921 0.01941 0.01035 -0.0248 0.1575 1.0000
7.750 1.0128 0.01974 0.01074 -0.0238 0.1537 1.0000
8.000 1.0326 0.02013 0.01113 -0.0225 0.1500 1.0000
8.250 1.0522 0.02057 0.01158 -0.0213 0.1463 1.0000
8.500 1.0726 0.02085 0.01199 -0.0202 0.1423 1.0000
8.750 1.0923 0.02118 0.01240 -0.0190 0.1383 1.0000
9.000 1.1107 0.02157 0.01282 -0.0176 0.1347 1.0000
9.250 1.1291 0.02201 0.01331 -0.0162 0.1316 1.0000
9.500 1.1486 0.02238 0.01382 -0.0150 0.1281 1.0000
9.750 1.1669 0.02277 0.01431 -0.0136 0.1245 1.0000
10.000 1.1824 0.02319 0.01479 -0.0118 0.1211 1.0000
10.250 1.1975 0.02361 0.01528 -0.0099 0.1173 1.0000
10.500 1.2138 0.02399 0.01578 -0.0083 0.1118 1.0000
10.750 1.2275 0.02443 0.01625 -0.0063 0.1070 1.0000
11.000 1.2438 0.02492 0.01687 -0.0048 0.1021 1.0000
11.250 1.2587 0.02545 0.01748 -0.0031 0.0972 1.0000
11.500 1.2729 0.02606 0.01815 -0.0014 0.0928 1.0000
11.750 1.2874 0.02670 0.01887 0.0001 0.0869 1.0000
12.000 1.3003 0.02744 0.01966 0.0018 0.0814 1.0000
12.250 1.3132 0.02824 0.02056 0.0034 0.0762 1.0000
12.500 1.3241 0.02917 0.02154 0.0051 0.0716 1.0000
12.750 1.3354 0.03014 0.02261 0.0068 0.0666 1.0000
13.000 1.3435 0.03132 0.02384 0.0086 0.0621 1.0000
13.250 1.3529 0.03247 0.02511 0.0103 0.0575 1.0000
13.500 1.3581 0.03392 0.02663 0.0122 0.0532 1.0000
13.750 1.3648 0.03530 0.02817 0.0138 0.0490 1.0000
14.000 1.3679 0.03700 0.02996 0.0156 0.0451 1.0000
14.250 1.3704 0.03879 0.03187 0.0173 0.0420 1.0000
14.500 1.3711 0.04078 0.03399 0.0189 0.0392 1.0000
14.750 1.3683 0.04315 0.03646 0.0203 0.0372 1.0000
15.000 1.3655 0.04565 0.03910 0.0215 0.0356 1.0000
15.250 1.3611 0.04845 0.04206 0.0223 0.0343 1.0000
15.500 1.3540 0.05175 0.04551 0.0226 0.0333 1.0000
15.750 1.3444 0.05566 0.04958 0.0223 0.0325 1.0000
16.000 1.3320 0.06035 0.05443 0.0212 0.0319 1.0000
16.250 1.3163 0.06600 0.06025 0.0192 0.0315 1.0000
16.500 1.2971 0.07269 0.06712 0.0162 0.0312 1.0000
16.750 1.2738 0.08051 0.07513 0.0124 0.0311 1.0000
17.000 1.2465 0.08938 0.08420 0.0080 0.0311 1.0000
17.250 1.2170 0.09874 0.09374 0.0034 0.0312 1.0000
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Polar data table (+)
Polar graphs
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