BOEING-VERTOL VR-8 AIRFOIL WITH TAB (vr8b-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-8 AIRFOIL WITH TAB (vr8b-il) Reynolds number: 100,000 Max Cl/Cd: 37.11 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-vr8b-il-100000-n5.txt Download as CSV file: xf-vr8b-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BOEING-VERTOL VR-8 AIRFOIL WITH TAB
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.6486 0.09721 0.09292 0.0197 1.0000 0.0525
-8.000 -0.6518 0.09083 0.08657 0.0088 1.0000 0.0536
-7.750 -0.6538 0.08495 0.08047 -0.0013 1.0000 0.0544
-7.000 -0.6247 0.06427 0.05947 -0.0078 1.0000 0.0316
-6.750 -0.6147 0.05596 0.05066 -0.0112 1.0000 0.0263
-6.500 -0.5991 0.05190 0.04648 -0.0122 1.0000 0.0256
-6.250 -0.5810 0.04710 0.04134 -0.0136 1.0000 0.0253
-6.000 -0.5596 0.04199 0.03558 -0.0147 1.0000 0.0261
-5.750 -0.5361 0.03757 0.03046 -0.0153 1.0000 0.0264
-5.500 -0.5112 0.03389 0.02639 -0.0158 1.0000 0.0262
-5.250 -0.4845 0.03050 0.02245 -0.0161 1.0000 0.0262
-5.000 -0.4563 0.02750 0.01892 -0.0162 1.0000 0.0265
-4.750 -0.4293 0.02582 0.01719 -0.0168 1.0000 0.0288
-4.500 -0.4001 0.02411 0.01509 -0.0169 1.0000 0.0316
-4.250 -0.3708 0.02227 0.01293 -0.0169 1.0000 0.0324
-4.000 -0.3427 0.02045 0.01105 -0.0171 1.0000 0.0339
-3.750 -0.3147 0.01935 0.00990 -0.0175 1.0000 0.0376
-3.500 -0.2865 0.01818 0.00867 -0.0176 1.0000 0.0388
-3.250 -0.2584 0.01718 0.00763 -0.0179 1.0000 0.0398
-3.000 -0.2301 0.01639 0.00675 -0.0182 1.0000 0.0410
-2.750 -0.2016 0.01577 0.00602 -0.0187 1.0000 0.0425
-2.500 -0.1703 0.01513 0.00530 -0.0198 0.9882 0.0462
-2.250 -0.1334 0.01469 0.00482 -0.0220 0.9695 0.0557
-2.000 -0.1018 0.01419 0.00444 -0.0229 0.9450 0.0902
-1.750 -0.0847 0.01181 0.00437 -0.0212 0.9104 0.6249
-1.500 -0.0685 0.01152 0.00427 -0.0174 0.8714 0.7210
-1.250 -0.0536 0.01136 0.00417 -0.0132 0.8382 0.7912
-1.000 -0.0374 0.01125 0.00404 -0.0092 0.8090 0.8625
-0.750 -0.0125 0.01119 0.00386 -0.0078 0.7890 0.9138
-0.500 0.0152 0.01120 0.00366 -0.0073 0.7669 0.9539
-0.250 0.0477 0.01119 0.00339 -0.0080 0.7401 0.9842
0.000 0.0771 0.01122 0.00319 -0.0083 0.7159 1.0000
0.250 0.1037 0.01132 0.00308 -0.0081 0.6911 1.0000
0.500 0.1307 0.01143 0.00300 -0.0079 0.6707 1.0000
0.750 0.1587 0.01152 0.00298 -0.0081 0.6573 1.0000
1.000 0.1870 0.01162 0.00300 -0.0083 0.6461 1.0000
1.250 0.2153 0.01173 0.00303 -0.0085 0.6358 1.0000
1.500 0.2435 0.01184 0.00311 -0.0087 0.6263 1.0000
1.750 0.2721 0.01195 0.00320 -0.0090 0.6169 1.0000
2.000 0.3005 0.01208 0.00331 -0.0092 0.6082 1.0000
2.250 0.3292 0.01221 0.00344 -0.0095 0.5989 1.0000
2.500 0.3580 0.01235 0.00363 -0.0098 0.5875 1.0000
2.750 0.3865 0.01250 0.00377 -0.0100 0.5709 1.0000
3.000 0.4146 0.01266 0.00387 -0.0101 0.5424 1.0000
3.250 0.4427 0.01285 0.00398 -0.0102 0.5079 1.0000
3.500 0.4711 0.01306 0.00419 -0.0104 0.4685 1.0000
3.750 0.4988 0.01344 0.00433 -0.0106 0.3955 1.0000
4.000 0.5258 0.01429 0.00464 -0.0111 0.2777 1.0000
4.250 0.5530 0.01531 0.00525 -0.0119 0.1808 1.0000
4.500 0.5791 0.01685 0.00610 -0.0129 0.0602 1.0000
4.750 0.6065 0.01761 0.00685 -0.0133 0.0475 1.0000
5.000 0.6339 0.01832 0.00764 -0.0136 0.0438 1.0000
5.250 0.6611 0.01908 0.00853 -0.0138 0.0416 1.0000
5.500 0.6880 0.01983 0.00947 -0.0140 0.0403 1.0000
5.750 0.7142 0.02070 0.01053 -0.0141 0.0392 1.0000
6.000 0.7397 0.02170 0.01175 -0.0141 0.0384 1.0000
6.250 0.7645 0.02285 0.01305 -0.0139 0.0377 1.0000
6.500 0.7888 0.02416 0.01448 -0.0136 0.0368 1.0000
6.750 0.8123 0.02558 0.01591 -0.0135 0.0341 1.0000
7.000 0.8364 0.02724 0.01772 -0.0131 0.0324 1.0000
7.250 0.8611 0.02846 0.01916 -0.0130 0.0288 1.0000
7.500 0.8847 0.03046 0.02135 -0.0126 0.0273 1.0000
7.750 0.9082 0.03286 0.02404 -0.0121 0.0258 1.0000
8.000 0.9296 0.03508 0.02643 -0.0120 0.0237 1.0000
8.250 0.9501 0.03790 0.02949 -0.0117 0.0223 1.0000
8.500 0.9686 0.04166 0.03351 -0.0114 0.0217 1.0000
8.750 0.9807 0.04602 0.03867 -0.0106 0.0215 1.0000
9.000 0.9885 0.05063 0.04389 -0.0100 0.0215 1.0000
9.250 0.9918 0.05534 0.04911 -0.0095 0.0215 1.0000
9.500 0.9875 0.06024 0.05452 -0.0093 0.0215 1.0000
9.750 0.9777 0.06508 0.05975 -0.0095 0.0214 1.0000
10.000 0.9634 0.06954 0.06446 -0.0100 0.0214 1.0000
10.250 0.9483 0.07432 0.06941 -0.0119 0.0215 1.0000
10.500 0.9346 0.07971 0.07494 -0.0152 0.0216 1.0000
10.750 0.9231 0.08548 0.08080 -0.0190 0.0218 1.0000
11.000 0.8822 0.10094 0.09649 -0.0327 0.0239 1.0000
11.250 0.8739 0.10886 0.10441 -0.0376 0.0243 1.0000
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Polar data table (+)
Polar graphs
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