E180 (8.59%) (e180-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: E180 (8.59%) (e180-il) Reynolds number: 500,000 Max Cl/Cd: 93.66 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e180-il-500000.txt Download as CSV file: xf-e180-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: E180 (8.59%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5109 0.08528 0.08327 -0.0028 1.0000 0.0168
-8.000 -0.5118 0.08109 0.07913 -0.0055 1.0000 0.0172
-7.750 -0.5153 0.07690 0.07499 -0.0086 1.0000 0.0174
-7.500 -0.5164 0.07186 0.06997 -0.0137 1.0000 0.0176
-7.250 -0.5117 0.06579 0.06387 -0.0199 1.0000 0.0181
-7.000 -0.5009 0.05910 0.05709 -0.0258 1.0000 0.0189
-6.750 -0.4759 0.05267 0.05039 -0.0317 0.9404 0.0196
-6.500 -0.4698 0.04843 0.04581 -0.0316 0.8995 0.0197
-5.000 -0.3860 0.01946 0.01406 -0.0271 0.8056 0.0128
-4.750 -0.3622 0.01689 0.01103 -0.0262 0.7953 0.0126
-4.500 -0.3366 0.01542 0.00927 -0.0254 0.7858 0.0129
-4.250 -0.3103 0.01450 0.00812 -0.0249 0.7766 0.0133
-4.000 -0.2855 0.01290 0.00633 -0.0242 0.7678 0.0140
-3.750 -0.2600 0.01205 0.00538 -0.0237 0.7599 0.0155
-3.500 -0.2337 0.01137 0.00459 -0.0233 0.7515 0.0162
-3.250 -0.2072 0.01082 0.00392 -0.0228 0.7442 0.0172
-3.000 -0.1801 0.01038 0.00337 -0.0225 0.7366 0.0193
-2.750 -0.1537 0.00971 0.00268 -0.0220 0.7298 0.0367
-2.500 -0.1273 0.00921 0.00239 -0.0218 0.7228 0.0939
-2.250 -0.1008 0.00883 0.00219 -0.0216 0.7163 0.1560
-2.000 -0.0748 0.00833 0.00204 -0.0215 0.7095 0.2562
-1.750 -0.0498 0.00777 0.00192 -0.0212 0.7037 0.3928
-1.500 -0.0247 0.00728 0.00182 -0.0208 0.6970 0.5162
-1.250 -0.0017 0.00675 0.00174 -0.0198 0.6914 0.6631
-1.000 0.0189 0.00616 0.00173 -0.0179 0.6853 0.8281
-0.750 0.0717 0.00601 0.00177 -0.0225 0.6794 0.9597
-0.500 0.1190 0.00608 0.00173 -0.0266 0.6735 0.9867
-0.250 0.1699 0.00609 0.00165 -0.0316 0.6672 1.0000
0.000 0.1956 0.00614 0.00159 -0.0311 0.6617 1.0000
0.250 0.2216 0.00615 0.00157 -0.0307 0.6554 1.0000
0.500 0.2476 0.00620 0.00154 -0.0303 0.6498 1.0000
0.750 0.2738 0.00624 0.00154 -0.0300 0.6437 1.0000
1.000 0.3000 0.00628 0.00153 -0.0296 0.6375 1.0000
1.250 0.3263 0.00634 0.00155 -0.0293 0.6313 1.0000
1.500 0.3527 0.00638 0.00156 -0.0289 0.6241 1.0000
1.750 0.3790 0.00644 0.00157 -0.0286 0.6171 1.0000
2.000 0.4055 0.00648 0.00159 -0.0283 0.6092 1.0000
2.250 0.4320 0.00653 0.00163 -0.0279 0.6012 1.0000
2.500 0.4584 0.00659 0.00167 -0.0276 0.5935 1.0000
2.750 0.4851 0.00664 0.00173 -0.0273 0.5849 1.0000
3.000 0.5115 0.00671 0.00178 -0.0270 0.5764 1.0000
3.250 0.5382 0.00676 0.00183 -0.0267 0.5665 1.0000
3.500 0.5648 0.00683 0.00193 -0.0264 0.5561 1.0000
3.750 0.5914 0.00690 0.00201 -0.0262 0.5456 1.0000
4.000 0.6178 0.00698 0.00208 -0.0258 0.5299 1.0000
4.250 0.6439 0.00709 0.00213 -0.0255 0.5050 1.0000
4.500 0.6700 0.00724 0.00226 -0.0251 0.4817 1.0000
4.750 0.6959 0.00743 0.00239 -0.0248 0.4514 1.0000
5.000 0.7212 0.00774 0.00257 -0.0245 0.4077 1.0000
5.250 0.7445 0.00840 0.00289 -0.0240 0.3285 1.0000
5.500 0.7662 0.00937 0.00342 -0.0236 0.2331 1.0000
5.750 0.7882 0.01027 0.00396 -0.0231 0.1574 1.0000
6.000 0.8101 0.01117 0.00453 -0.0226 0.0941 1.0000
6.250 0.8302 0.01234 0.00532 -0.0219 0.0310 1.0000
6.500 0.8536 0.01296 0.00596 -0.0212 0.0232 1.0000
6.750 0.8769 0.01358 0.00664 -0.0206 0.0204 1.0000
7.000 0.8980 0.01452 0.00769 -0.0197 0.0181 1.0000
7.250 0.9199 0.01525 0.00851 -0.0189 0.0176 1.0000
7.500 0.9410 0.01607 0.00942 -0.0181 0.0171 1.0000
7.750 0.9613 0.01695 0.01040 -0.0171 0.0165 1.0000
8.000 0.9805 0.01797 0.01152 -0.0160 0.0160 1.0000
8.250 0.9989 0.01910 0.01277 -0.0148 0.0155 1.0000
8.500 1.0177 0.02014 0.01389 -0.0137 0.0147 1.0000
8.750 1.0360 0.02125 0.01507 -0.0126 0.0139 1.0000
9.000 1.0533 0.02258 0.01649 -0.0114 0.0134 1.0000
9.250 1.0698 0.02427 0.01829 -0.0102 0.0130 1.0000
9.500 1.0858 0.02647 0.02064 -0.0089 0.0127 1.0000
9.750 1.1003 0.02946 0.02385 -0.0076 0.0124 1.0000
10.000 1.1113 0.03306 0.02777 -0.0061 0.0122 1.0000
10.250 1.1152 0.03741 0.03248 -0.0042 0.0120 1.0000
10.500 1.1266 0.03668 0.03195 -0.0025 0.0112 1.0000
10.750 1.1285 0.03914 0.03466 -0.0003 0.0110 1.0000
11.000 1.1232 0.04152 0.03726 0.0025 0.0108 1.0000
11.250 1.1116 0.04476 0.04075 0.0047 0.0109 1.0000
11.500 1.0957 0.04875 0.04498 0.0060 0.0111 1.0000
11.750 1.0813 0.05261 0.04905 0.0064 0.0111 1.0000
12.000 1.0635 0.05726 0.05390 0.0059 0.0112 1.0000
12.250 1.0479 0.06189 0.05871 0.0045 0.0112 1.0000
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Polar data table (+)
Polar graphs
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