E10(08%) (e228-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: E10(08%) (e228-il) Reynolds number: 200,000 Max Cl/Cd: 51.61 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e228-il-200000.txt Download as CSV file: xf-e228-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: E10(08%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.6712 0.09316 0.08987 -0.0011 1.0000 0.0653
-10.000 -0.7206 0.05403 0.05061 -0.0251 1.0000 0.0361
-9.750 -0.7447 0.04931 0.04576 -0.0255 1.0000 0.0354
-9.500 -0.8599 0.05000 0.04534 -0.0192 1.0000 0.0286
-9.250 -0.8647 0.04537 0.04039 -0.0175 1.0000 0.0290
-9.000 -0.8612 0.04181 0.03644 -0.0156 1.0000 0.0289
-8.750 -0.8503 0.03927 0.03355 -0.0138 1.0000 0.0284
-8.500 -0.8370 0.03672 0.03067 -0.0122 1.0000 0.0282
-8.250 -0.8242 0.03344 0.02700 -0.0106 1.0000 0.0281
-8.000 -0.8111 0.02931 0.02240 -0.0089 1.0000 0.0285
-7.750 -0.7932 0.02595 0.01875 -0.0077 1.0000 0.0294
-7.500 -0.7727 0.02427 0.01700 -0.0069 1.0000 0.0315
-7.250 -0.7508 0.02304 0.01565 -0.0060 1.0000 0.0342
-7.000 -0.7281 0.02155 0.01398 -0.0049 1.0000 0.0360
-6.750 -0.7051 0.02038 0.01265 -0.0039 1.0000 0.0377
-6.500 -0.6865 0.01853 0.01083 -0.0025 1.0000 0.0416
-6.250 -0.6654 0.01761 0.00987 -0.0014 1.0000 0.0458
-6.000 -0.6454 0.01662 0.00879 0.0001 1.0000 0.0500
-5.750 -0.6275 0.01558 0.00778 0.0018 1.0000 0.0589
-5.500 -0.6118 0.01441 0.00678 0.0039 1.0000 0.0833
-5.250 -0.5977 0.01326 0.00603 0.0061 1.0000 0.1473
-5.000 -0.5807 0.01266 0.00562 0.0079 1.0000 0.1955
-4.750 -0.5640 0.01216 0.00529 0.0097 1.0000 0.2413
-4.500 -0.5478 0.01172 0.00503 0.0116 1.0000 0.2867
-4.250 -0.5319 0.01133 0.00484 0.0135 1.0000 0.3375
-4.000 -0.5163 0.01097 0.00468 0.0155 1.0000 0.3878
-3.750 -0.5001 0.01068 0.00456 0.0175 1.0000 0.4355
-3.500 -0.4834 0.01045 0.00446 0.0193 1.0000 0.4791
-3.250 -0.4490 0.01021 0.00440 0.0176 0.9946 0.5340
-3.000 -0.4098 0.00996 0.00435 0.0151 0.9866 0.5913
-2.750 -0.3704 0.00977 0.00432 0.0128 0.9791 0.6446
-2.500 -0.3299 0.00960 0.00429 0.0104 0.9719 0.6944
-2.250 -0.2909 0.00947 0.00428 0.0084 0.9641 0.7391
-2.000 -0.2485 0.00937 0.00427 0.0059 0.9579 0.7797
-1.750 -0.2115 0.00932 0.00429 0.0046 0.9487 0.8149
-1.500 -0.1711 0.00930 0.00432 0.0027 0.9413 0.8454
-1.250 -0.1358 0.00933 0.00435 0.0020 0.9305 0.8720
-1.000 -0.0996 0.00940 0.00441 0.0011 0.9191 0.8934
-0.750 -0.0650 0.00948 0.00446 0.0006 0.9069 0.9125
-0.500 -0.0286 0.00957 0.00451 -0.0004 0.8944 0.9273
-0.250 0.0128 0.00967 0.00456 -0.0024 0.8815 0.9375
0.000 0.0545 0.00974 0.00458 -0.0046 0.8670 0.9470
0.250 0.0936 0.00980 0.00458 -0.0064 0.8507 0.9579
0.500 0.1334 0.00983 0.00456 -0.0084 0.8334 0.9685
0.750 0.1769 0.00981 0.00447 -0.0113 0.8152 0.9770
1.000 0.2191 0.00976 0.00437 -0.0141 0.7947 0.9865
1.250 0.2620 0.00966 0.00421 -0.0171 0.7730 0.9953
1.500 0.2957 0.00954 0.00403 -0.0184 0.7498 1.0000
1.750 0.3154 0.00951 0.00393 -0.0169 0.7281 1.0000
2.000 0.3360 0.00950 0.00386 -0.0155 0.7042 1.0000
2.250 0.3570 0.00952 0.00380 -0.0142 0.6805 1.0000
2.500 0.3784 0.00956 0.00375 -0.0129 0.6560 1.0000
2.750 0.4003 0.00962 0.00376 -0.0117 0.6293 1.0000
3.000 0.4224 0.00971 0.00378 -0.0106 0.6020 1.0000
3.250 0.4447 0.00984 0.00383 -0.0095 0.5738 1.0000
3.500 0.4670 0.00999 0.00390 -0.0083 0.5442 1.0000
3.750 0.4894 0.01018 0.00402 -0.0073 0.5137 1.0000
4.000 0.5118 0.01039 0.00415 -0.0062 0.4814 1.0000
4.250 0.5342 0.01063 0.00432 -0.0052 0.4473 1.0000
4.500 0.5563 0.01093 0.00451 -0.0042 0.4125 1.0000
4.750 0.5784 0.01125 0.00474 -0.0032 0.3743 1.0000
5.000 0.6002 0.01163 0.00502 -0.0022 0.3348 1.0000
5.250 0.6217 0.01208 0.00533 -0.0011 0.2931 1.0000
5.500 0.6428 0.01259 0.00570 -0.0001 0.2498 1.0000
5.750 0.6634 0.01319 0.00613 0.0009 0.2066 1.0000
6.000 0.6835 0.01389 0.00665 0.0021 0.1660 1.0000
6.250 0.7027 0.01471 0.00731 0.0033 0.1316 1.0000
6.500 0.7216 0.01560 0.00805 0.0046 0.1033 1.0000
6.750 0.7409 0.01643 0.00883 0.0059 0.0808 1.0000
7.000 0.7583 0.01750 0.00981 0.0074 0.0640 1.0000
7.250 0.7761 0.01855 0.01087 0.0090 0.0508 1.0000
7.500 0.7921 0.01983 0.01212 0.0107 0.0409 1.0000
7.750 0.8106 0.02087 0.01331 0.0123 0.0352 1.0000
8.000 0.8238 0.02318 0.01558 0.0143 0.0311 1.0000
8.250 0.8437 0.02407 0.01667 0.0157 0.0283 1.0000
8.500 0.8621 0.02518 0.01789 0.0170 0.0257 1.0000
8.750 0.8791 0.02682 0.01961 0.0184 0.0241 1.0000
9.000 0.8939 0.02966 0.02261 0.0198 0.0230 1.0000
9.250 0.9048 0.03332 0.02662 0.0216 0.0225 1.0000
9.500 0.9156 0.03582 0.02946 0.0235 0.0223 1.0000
9.750 0.9219 0.03870 0.03271 0.0255 0.0221 1.0000
10.000 0.9232 0.04204 0.03643 0.0277 0.0222 1.0000
10.250 0.9187 0.04581 0.04052 0.0299 0.0223 1.0000
10.500 0.9125 0.04994 0.04491 0.0317 0.0226 1.0000
10.750 0.9049 0.05220 0.04737 0.0342 0.0228 1.0000
11.000 0.8940 0.05457 0.04992 0.0361 0.0230 1.0000
11.250 0.8816 0.05729 0.05285 0.0367 0.0233 1.0000
11.500 0.8582 0.06189 0.05773 0.0353 0.0238 1.0000
11.750 0.8208 0.06981 0.06597 0.0299 0.0246 1.0000
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Polar data table (+)
Polar graphs
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