BOEING-VERTOL VR-8 AIRFOIL WITH TAB (vr8b-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: BOEING-VERTOL VR-8 AIRFOIL WITH TAB (vr8b-il) Reynolds number: 1,000,000 Max Cl/Cd: 62.04 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-vr8b-il-1000000-n5.txt Download as CSV file: xf-vr8b-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.7287 0.09117 0.08984 0.0346 1.0000 0.0024
-8.500 -0.7362 0.08394 0.08264 0.0281 1.0000 0.0024
-8.250 -0.7441 0.07357 0.07222 0.0148 0.9772 0.0024
-8.000 -0.7474 0.06450 0.06300 0.0077 0.9705 0.0024
-7.750 -0.7459 0.05696 0.05527 0.0042 0.9647 0.0025
-7.500 -0.7385 0.04949 0.04754 0.0018 0.9598 0.0026
-7.250 -0.7278 0.04232 0.04005 0.0007 0.9547 0.0028
-7.000 -0.7287 0.02070 0.01676 0.0009 0.9508 0.0035
-6.750 -0.7037 0.01676 0.01223 0.0008 0.9451 0.0038
-6.500 -0.6772 0.01490 0.01005 0.0008 0.9368 0.0040
-6.000 -0.6280 0.01327 0.00810 0.0020 0.9111 0.0050
-5.750 -0.6026 0.01319 0.00797 0.0025 0.8929 0.0056
-5.500 -0.5764 0.01292 0.00758 0.0029 0.8688 0.0062
-5.250 -0.5494 0.01233 0.00682 0.0030 0.8435 0.0069
-5.000 -0.5213 0.01236 0.00674 0.0029 0.8168 0.0074
-4.750 -0.4927 0.01232 0.00655 0.0026 0.7812 0.0081
-4.500 -0.4627 0.01224 0.00608 0.0021 0.6998 0.0096
-4.250 -0.4327 0.01213 0.00568 0.0015 0.6452 0.0107
-4.000 -0.4029 0.01213 0.00550 0.0007 0.5947 0.0113
-3.500 -0.3365 0.01310 0.00486 -0.0030 0.0394 0.0132
-3.250 -0.3072 0.01307 0.00472 -0.0033 0.0357 0.0138
-3.000 -0.2781 0.01274 0.00432 -0.0038 0.0333 0.0145
-2.750 -0.2487 0.01223 0.00378 -0.0043 0.0234 0.0149
-2.500 -0.2194 0.01184 0.00339 -0.0049 0.0203 0.0154
-2.250 -0.1898 0.01157 0.00309 -0.0054 0.0194 0.0156
-2.000 -0.1602 0.01136 0.00283 -0.0059 0.0191 0.0156
-1.750 -0.1305 0.01116 0.00260 -0.0064 0.0189 0.0157
-1.500 -0.1008 0.01098 0.00239 -0.0069 0.0189 0.0160
-1.250 -0.0711 0.01084 0.00222 -0.0074 0.0189 0.0163
-1.000 -0.0414 0.01072 0.00208 -0.0080 0.0189 0.0168
-0.750 -0.0117 0.01064 0.00199 -0.0085 0.0190 0.0173
-0.500 0.0179 0.01059 0.00193 -0.0089 0.0191 0.0178
-0.250 0.0475 0.01058 0.00190 -0.0094 0.0193 0.0180
0.000 0.0772 0.01054 0.00184 -0.0099 0.0194 0.0183
0.250 0.1068 0.01052 0.00180 -0.0104 0.0196 0.0185
0.500 0.1365 0.01055 0.00181 -0.0110 0.0194 0.0194
0.750 0.1661 0.01058 0.00183 -0.0114 0.0188 0.0198
1.000 0.1956 0.01063 0.00189 -0.0119 0.0184 0.0197
1.250 0.2252 0.01070 0.00197 -0.0124 0.0182 0.0197
1.500 0.2547 0.01079 0.00207 -0.0129 0.0180 0.0198
1.750 0.2843 0.01091 0.00220 -0.0135 0.0176 0.0200
2.000 0.3139 0.01107 0.00237 -0.0140 0.0173 0.0203
2.250 0.3438 0.01139 0.00269 -0.0147 0.0168 0.0209
2.750 0.4028 0.01187 0.00322 -0.0159 0.0160 0.0321
3.000 0.4321 0.01210 0.00346 -0.0165 0.0159 0.0330
3.250 0.4613 0.01234 0.00372 -0.0170 0.0158 0.0375
3.500 0.4905 0.01264 0.00406 -0.0175 0.0158 0.0406
3.750 0.5195 0.01302 0.00446 -0.0181 0.0159 0.0424
4.000 0.5523 0.01246 0.00504 -0.0204 0.0160 0.5601
4.500 0.6085 0.01179 0.00553 -0.0209 0.0172 0.8824
4.750 0.6289 0.01187 0.00578 -0.0191 0.0178 0.9344
5.000 0.6553 0.01234 0.00626 -0.0191 0.0184 0.9566
5.500 0.7059 0.01337 0.00732 -0.0185 0.0152 1.0000
5.750 0.7340 0.01384 0.00781 -0.0190 0.0144 1.0000
6.000 0.7601 0.01509 0.00883 -0.0192 0.0135 1.0000
6.250 0.7885 0.01529 0.00917 -0.0197 0.0130 1.0000
6.500 0.8176 0.01517 0.00925 -0.0201 0.0122 1.0000
6.750 0.8459 0.01530 0.00946 -0.0205 0.0111 1.0000
7.000 0.8740 0.01539 0.00956 -0.0210 0.0103 1.0000
7.250 0.9022 0.01564 0.01001 -0.0213 0.0085 1.0000
7.500 0.9299 0.01595 0.01038 -0.0216 0.0066 1.0000
7.750 0.9585 0.01577 0.01017 -0.0221 0.0058 1.0000
8.000 0.9864 0.01590 0.01030 -0.0224 0.0048 1.0000
8.250 1.0125 0.01663 0.01111 -0.0227 0.0044 1.0000
8.500 1.0382 0.01744 0.01201 -0.0228 0.0040 1.0000
8.750 1.0637 0.01822 0.01289 -0.0230 0.0035 1.0000
9.000 1.0890 0.01899 0.01374 -0.0231 0.0031 1.0000
9.250 1.1137 0.01987 0.01474 -0.0232 0.0027 1.0000
9.500 1.1374 0.02096 0.01598 -0.0231 0.0025 1.0000
9.750 1.1607 0.02202 0.01718 -0.0231 0.0024 1.0000
10.000 1.1832 0.02318 0.01850 -0.0230 0.0024 1.0000
10.250 1.2047 0.02450 0.01998 -0.0228 0.0023 1.0000
10.500 1.2249 0.02594 0.02162 -0.0225 0.0022 1.0000
10.750 1.2437 0.02756 0.02343 -0.0222 0.0021 1.0000
11.000 1.2606 0.02933 0.02541 -0.0217 0.0020 1.0000
11.250 1.2753 0.03131 0.02761 -0.0211 0.0019 1.0000
11.500 1.2870 0.03351 0.03003 -0.0204 0.0019 1.0000
11.750 1.2956 0.03586 0.03261 -0.0196 0.0018 1.0000
12.000 1.2993 0.03852 0.03550 -0.0186 0.0017 1.0000
12.250 1.2916 0.04156 0.03877 -0.0170 0.0017 1.0000
12.500 1.2828 0.04482 0.04221 -0.0165 0.0017 1.0000
12.750 1.2703 0.04925 0.04685 -0.0178 0.0017 1.0000
13.000 1.2584 0.05427 0.05205 -0.0203 0.0016 1.0000
13.250 1.2371 0.06145 0.05944 -0.0247 0.0016 1.0000
13.500 1.2078 0.07081 0.06902 -0.0309 0.0017 1.0000
13.750 1.1716 0.08271 0.08112 -0.0390 0.0017 1.0000
|
Polar data table (+)
Polar graphs
<< Back to BOEING-VERTOL VR-8 AIRFOIL WITH TAB (vr8b-il)