E230 (9.96%) (e230-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: E230 (9.96%) (e230-il) Reynolds number: 100,000 Max Cl/Cd: 32.24 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e230-il-100000-n5.txt Download as CSV file: xf-e230-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E230 (9.96%)
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
------ -------- --------- --------- -------- -------- --------
-12.000 -0.8311 0.09734 0.09263 0.0206 1.0000 0.0185
-11.750 -0.8675 0.08356 0.07871 0.0102 1.0000 0.0179
-11.500 -0.8975 0.07392 0.06887 0.0027 1.0000 0.0175
-11.250 -0.9227 0.06700 0.06172 -0.0016 1.0000 0.0174
-11.000 -0.9451 0.06163 0.05608 -0.0034 1.0000 0.0172
-10.750 -0.9635 0.05739 0.05157 -0.0031 1.0000 0.0172
-10.500 -0.9775 0.05386 0.04777 -0.0015 1.0000 0.0172
-10.250 -0.9872 0.05070 0.04432 0.0009 1.0000 0.0172
-10.000 -0.9904 0.04761 0.04090 0.0031 1.0000 0.0173
-9.750 -0.9879 0.04466 0.03761 0.0049 1.0000 0.0174
-9.500 -0.9810 0.04189 0.03449 0.0066 1.0000 0.0176
-9.250 -0.9706 0.03929 0.03158 0.0082 1.0000 0.0179
-9.000 -0.9570 0.03706 0.02907 0.0095 1.0000 0.0184
-8.750 -0.9414 0.03503 0.02676 0.0108 1.0000 0.0194
-8.500 -0.9237 0.03308 0.02450 0.0120 1.0000 0.0204
-8.250 -0.9053 0.03116 0.02236 0.0131 1.0000 0.0212
-8.000 -0.8876 0.02937 0.02049 0.0142 1.0000 0.0219
-7.750 -0.8694 0.02784 0.01883 0.0154 1.0000 0.0227
-7.500 -0.8509 0.02644 0.01730 0.0166 1.0000 0.0238
-7.250 -0.8322 0.02513 0.01585 0.0179 1.0000 0.0252
-7.000 -0.8129 0.02393 0.01446 0.0192 1.0000 0.0270
-6.750 -0.7943 0.02267 0.01313 0.0205 1.0000 0.0300
-6.500 -0.7740 0.02157 0.01195 0.0216 1.0000 0.0365
-6.250 -0.7551 0.02024 0.01068 0.0229 1.0000 0.0515
-6.000 -0.7355 0.01901 0.00965 0.0240 1.0000 0.0864
-5.750 -0.7153 0.01798 0.00893 0.0249 1.0000 0.1381
-5.500 -0.6955 0.01703 0.00837 0.0258 1.0000 0.2027
-5.250 -0.6747 0.01629 0.00785 0.0267 1.0000 0.2565
-5.000 -0.6526 0.01571 0.00738 0.0276 1.0000 0.2977
-4.750 -0.6303 0.01520 0.00696 0.0285 1.0000 0.3382
-4.500 -0.6082 0.01471 0.00658 0.0295 1.0000 0.3782
-4.250 -0.5861 0.01426 0.00622 0.0305 1.0000 0.4177
-4.000 -0.5641 0.01385 0.00593 0.0316 1.0000 0.4581
-3.750 -0.5425 0.01348 0.00568 0.0328 1.0000 0.4985
-3.500 -0.5212 0.01314 0.00547 0.0341 1.0000 0.5381
-3.250 -0.5005 0.01284 0.00528 0.0355 1.0000 0.5777
-3.000 -0.4803 0.01259 0.00515 0.0371 1.0000 0.6169
-2.750 -0.4600 0.01239 0.00507 0.0386 1.0000 0.6555
-2.500 -0.4242 0.01226 0.00503 0.0371 0.9888 0.6987
-2.250 -0.3826 0.01220 0.00502 0.0347 0.9770 0.7401
-2.000 -0.3393 0.01221 0.00507 0.0319 0.9657 0.7761
-1.750 -0.2953 0.01226 0.00513 0.0291 0.9537 0.8066
-1.500 -0.2521 0.01236 0.00520 0.0265 0.9404 0.8320
-1.250 -0.2104 0.01247 0.00528 0.0242 0.9254 0.8531
-1.000 -0.1734 0.01258 0.00534 0.0229 0.9085 0.8725
-0.750 -0.1369 0.01270 0.00541 0.0218 0.8911 0.8884
-0.500 -0.1025 0.01282 0.00548 0.0210 0.8732 0.9031
-0.250 -0.0685 0.01292 0.00554 0.0203 0.8538 0.9167
0.000 -0.0319 0.01303 0.00560 0.0191 0.8342 0.9273
0.250 0.0027 0.01310 0.00562 0.0182 0.8144 0.9387
0.500 0.0369 0.01316 0.00564 0.0173 0.7926 0.9501
0.750 0.0704 0.01320 0.00564 0.0165 0.7708 0.9613
1.000 0.1050 0.01323 0.00563 0.0153 0.7477 0.9721
1.250 0.1420 0.01320 0.00556 0.0136 0.7237 0.9810
1.500 0.1791 0.01316 0.00549 0.0118 0.6971 0.9896
1.750 0.2164 0.01310 0.00540 0.0098 0.6690 0.9978
2.000 0.2424 0.01309 0.00534 0.0101 0.6417 1.0000
2.250 0.2642 0.01313 0.00532 0.0113 0.6144 1.0000
2.500 0.2865 0.01319 0.00532 0.0124 0.5861 1.0000
2.750 0.3091 0.01328 0.00537 0.0134 0.5566 1.0000
3.000 0.3319 0.01340 0.00543 0.0143 0.5256 1.0000
3.250 0.3550 0.01356 0.00553 0.0152 0.4929 1.0000
3.500 0.3780 0.01375 0.00568 0.0161 0.4586 1.0000
3.750 0.4011 0.01400 0.00585 0.0169 0.4235 1.0000
4.000 0.4244 0.01427 0.00606 0.0177 0.3866 1.0000
4.250 0.4475 0.01461 0.00631 0.0184 0.3480 1.0000
4.500 0.4705 0.01501 0.00664 0.0191 0.3077 1.0000
4.750 0.4934 0.01546 0.00700 0.0198 0.2669 1.0000
5.000 0.5159 0.01600 0.00742 0.0204 0.2229 1.0000
5.250 0.5377 0.01670 0.00788 0.0210 0.1712 1.0000
5.500 0.5588 0.01755 0.00844 0.0215 0.1186 1.0000
5.750 0.5802 0.01837 0.00913 0.0222 0.0829 1.0000
6.000 0.6005 0.01946 0.01009 0.0231 0.0557 1.0000
6.250 0.6203 0.02059 0.01118 0.0241 0.0421 1.0000
6.500 0.6401 0.02160 0.01225 0.0251 0.0354 1.0000
6.750 0.6588 0.02277 0.01353 0.0263 0.0324 1.0000
7.000 0.6775 0.02389 0.01483 0.0276 0.0303 1.0000
7.250 0.6955 0.02510 0.01614 0.0289 0.0287 1.0000
7.500 0.7129 0.02638 0.01751 0.0302 0.0275 1.0000
7.750 0.7294 0.02791 0.01909 0.0316 0.0266 1.0000
8.000 0.7463 0.02956 0.02089 0.0330 0.0258 1.0000
8.250 0.7633 0.03115 0.02275 0.0344 0.0246 1.0000
8.500 0.7789 0.03288 0.02475 0.0357 0.0234 1.0000
8.750 0.7929 0.03472 0.02683 0.0371 0.0225 1.0000
9.000 0.8049 0.03689 0.02926 0.0386 0.0221 1.0000
9.250 0.8141 0.03927 0.03191 0.0401 0.0218 1.0000
9.500 0.8202 0.04181 0.03474 0.0417 0.0215 1.0000
9.750 0.8223 0.04458 0.03781 0.0434 0.0214 1.0000
10.000 0.8198 0.04752 0.04102 0.0450 0.0213 1.0000
10.250 0.8116 0.05064 0.04440 0.0465 0.0212 1.0000
10.500 0.7948 0.05380 0.04777 0.0482 0.0213 1.0000
10.750 0.7752 0.05784 0.05202 0.0477 0.0214 1.0000
11.000 0.7519 0.06338 0.05777 0.0447 0.0216 1.0000
11.250 0.7161 0.07276 0.06739 0.0373 0.0220 1.0000
11.500 0.6690 0.08808 0.08283 0.0257 0.0229 1.0000
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Polar data table (+)
Polar graphs
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