BOEING-VERTOL VR-1 AIRFOIL (vr1-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-1 AIRFOIL (vr1-il) Reynolds number: 50,000 Max Cl/Cd: 30.59 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-vr1-il-50000.txt Download as CSV file: xf-vr1-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: BOEING-VERTOL VR-1 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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.4929 0.13614 0.12834 -0.0145 1.0000 0.2347
-11.250 -0.4612 0.12998 0.12210 -0.0132 1.0000 0.2423
-11.000 -0.4832 0.12946 0.12172 -0.0152 1.0000 0.2502
-10.750 -0.4526 0.12371 0.11589 -0.0140 1.0000 0.2589
-10.500 -0.4623 0.12155 0.11384 -0.0150 1.0000 0.2672
-10.250 -0.4535 0.11849 0.11078 -0.0147 1.0000 0.2795
-10.000 -0.4394 0.11439 0.10670 -0.0143 1.0000 0.2884
-9.750 -0.4504 0.11242 0.10483 -0.0148 1.0000 0.2995
-9.500 -0.4459 0.10979 0.10224 -0.0144 1.0000 0.3132
-9.250 -0.3259 0.09847 0.09148 -0.0191 1.0000 0.3258
-9.000 -0.3280 0.09525 0.08832 -0.0189 1.0000 0.3346
-8.750 -0.4373 0.10067 0.09329 -0.0131 1.0000 0.3484
-8.500 -0.4158 0.09656 0.08918 -0.0124 1.0000 0.3588
-8.250 -0.4121 0.09342 0.08610 -0.0118 1.0000 0.3696
-8.000 -0.4160 0.09093 0.08370 -0.0109 1.0000 0.3828
-7.750 -0.4072 0.08768 0.08050 -0.0104 1.0000 0.3902
-7.500 -0.4145 0.08500 0.07793 -0.0095 1.0000 0.3992
-7.250 -0.6106 0.06466 0.05729 -0.0333 1.0000 0.1704
-7.000 -0.6072 0.05939 0.05197 -0.0321 1.0000 0.1574
-6.750 -0.6064 0.05564 0.04800 -0.0301 1.0000 0.1489
-6.500 -0.6160 0.05137 0.04305 -0.0275 1.0000 0.1381
-6.250 -0.6082 0.04819 0.03972 -0.0254 1.0000 0.1349
-6.000 -0.6025 0.04491 0.03606 -0.0231 1.0000 0.1304
-5.750 -0.5968 0.04205 0.03226 -0.0201 1.0000 0.1248
-5.500 -0.5823 0.03964 0.02956 -0.0183 1.0000 0.1235
-5.250 -0.5666 0.03733 0.02698 -0.0165 1.0000 0.1228
-5.000 -0.5495 0.03527 0.02459 -0.0148 1.0000 0.1228
-4.750 -0.5313 0.03362 0.02252 -0.0130 1.0000 0.1241
-4.500 -0.5118 0.03172 0.02059 -0.0119 1.0000 0.1273
-4.250 -0.4913 0.03032 0.01910 -0.0106 1.0000 0.1313
-4.000 -0.4690 0.02902 0.01763 -0.0093 1.0000 0.1352
-3.750 -0.4457 0.02785 0.01626 -0.0080 1.0000 0.1402
-3.500 -0.4234 0.02670 0.01524 -0.0068 1.0000 0.1491
-3.250 -0.4019 0.02569 0.01429 -0.0054 1.0000 0.1642
-3.000 -0.3803 0.02438 0.01318 -0.0043 1.0000 0.1949
-2.750 -0.0974 0.02387 0.01520 -0.0328 1.0000 1.0000
-2.500 -0.1109 0.02346 0.01473 -0.0287 1.0000 1.0000
-2.250 -0.1230 0.02309 0.01428 -0.0244 1.0000 1.0000
-2.000 -0.1332 0.02276 0.01387 -0.0202 1.0000 1.0000
-1.750 -0.1409 0.02249 0.01348 -0.0161 1.0000 1.0000
-1.500 -0.1452 0.02229 0.01315 -0.0123 1.0000 1.0000
-1.250 -0.1456 0.02216 0.01288 -0.0089 1.0000 1.0000
-1.000 -0.1421 0.02213 0.01269 -0.0061 1.0000 1.0000
-0.750 -0.1354 0.02218 0.01258 -0.0036 1.0000 1.0000
-0.500 -0.1265 0.02230 0.01254 -0.0015 1.0000 1.0000
-0.250 -0.1156 0.02249 0.01256 0.0004 1.0000 1.0000
0.000 -0.1032 0.02273 0.01266 0.0020 1.0000 1.0000
0.250 -0.0896 0.02302 0.01283 0.0034 1.0000 1.0000
0.500 -0.0751 0.02336 0.01305 0.0046 1.0000 1.0000
0.750 -0.0600 0.02374 0.01333 0.0057 1.0000 1.0000
1.000 -0.0444 0.02416 0.01366 0.0067 1.0000 1.0000
1.250 -0.0285 0.02462 0.01404 0.0075 1.0000 1.0000
1.500 -0.0124 0.02512 0.01449 0.0083 1.0000 1.0000
1.750 0.0040 0.02567 0.01498 0.0090 1.0000 1.0000
2.000 0.0204 0.02625 0.01553 0.0096 1.0000 1.0000
2.250 0.0368 0.02688 0.01613 0.0102 1.0000 1.0000
2.500 0.0532 0.02756 0.01679 0.0107 1.0000 1.0000
2.750 0.0882 0.02883 0.01809 0.0074 0.9918 1.0000
3.000 0.1314 0.03034 0.01966 0.0027 0.9778 1.0000
3.250 0.1723 0.03176 0.02116 -0.0014 0.9631 1.0000
3.500 0.2123 0.03313 0.02264 -0.0052 0.9472 1.0000
3.750 0.2520 0.03447 0.02410 -0.0088 0.9303 1.0000
4.000 0.2964 0.03584 0.02564 -0.0129 0.9113 1.0000
4.250 0.3470 0.03677 0.02680 -0.0171 0.8807 1.0000
4.500 0.4877 0.03419 0.02486 -0.0283 0.7990 1.0000
4.750 0.6131 0.02867 0.02017 -0.0338 0.7392 1.0000
5.000 0.6692 0.02188 0.01358 -0.0240 0.5629 1.0000
5.250 0.6624 0.02387 0.01311 -0.0153 0.3019 1.0000
5.500 0.6739 0.02594 0.01448 -0.0125 0.2480 1.0000
5.750 0.7023 0.02777 0.01602 -0.0121 0.2138 1.0000
6.000 0.7404 0.02969 0.01769 -0.0132 0.1906 1.0000
6.250 0.7751 0.03162 0.01954 -0.0138 0.1750 1.0000
6.500 0.8060 0.03369 0.02181 -0.0138 0.1660 1.0000
6.750 0.8360 0.03615 0.02412 -0.0141 0.1574 1.0000
7.000 0.8555 0.03809 0.02655 -0.0124 0.1529 1.0000
7.250 0.8762 0.04054 0.02936 -0.0111 0.1503 1.0000
7.500 0.8945 0.04308 0.03223 -0.0096 0.1476 1.0000
7.750 0.9140 0.04579 0.03503 -0.0086 0.1441 1.0000
8.000 0.9306 0.04923 0.03861 -0.0075 0.1422 1.0000
8.250 0.9426 0.05248 0.04225 -0.0056 0.1425 1.0000
8.500 0.9346 0.05539 0.04599 -0.0014 0.1459 1.0000
8.750 0.9265 0.05950 0.05064 0.0016 0.1497 1.0000
9.000 0.9208 0.06374 0.05519 0.0039 0.1529 1.0000
9.250 0.9199 0.06813 0.05977 0.0054 0.1555 1.0000
9.500 0.8761 0.07310 0.06518 0.0086 0.1630 1.0000
9.750 0.8450 0.07839 0.07058 0.0102 0.1690 1.0000
10.000 0.7708 0.08779 0.08006 0.0062 0.1804 1.0000
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Polar data table (+)
Polar graphs
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