E168 (12.45%) (e168-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: E168 (12.45%) (e168-il) Reynolds number: 200,000 Max Cl/Cd: 52.82 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e168-il-200000-n5.txt Download as CSV file: xf-e168-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E168 (12.45%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.500 -0.8895 0.14812 0.14415 0.0273 1.0000 0.0133
-17.250 -0.9104 0.13793 0.13382 0.0215 1.0000 0.0132
-17.000 -0.9277 0.12912 0.12487 0.0165 1.0000 0.0132
-16.750 -0.9438 0.12092 0.11651 0.0118 1.0000 0.0132
-16.500 -0.9578 0.11342 0.10885 0.0075 1.0000 0.0134
-16.250 -0.9688 0.10691 0.10220 0.0040 1.0000 0.0134
-16.000 -0.9802 0.10039 0.09552 0.0004 1.0000 0.0135
-15.750 -0.9885 0.09491 0.08996 -0.0024 1.0000 0.0137
-15.500 -0.9968 0.08956 0.08452 -0.0052 1.0000 0.0139
-15.250 -1.0053 0.08422 0.07910 -0.0080 1.0000 0.0142
-15.000 -1.0127 0.07928 0.07405 -0.0105 1.0000 0.0143
-14.750 -1.0205 0.07444 0.06910 -0.0129 1.0000 0.0145
-14.500 -1.0283 0.06974 0.06430 -0.0152 1.0000 0.0147
-14.250 -1.0352 0.06530 0.05975 -0.0173 1.0000 0.0149
-14.000 -1.0414 0.06104 0.05538 -0.0193 1.0000 0.0152
-13.750 -1.0466 0.05700 0.05123 -0.0211 1.0000 0.0155
-13.500 -1.0510 0.05318 0.04728 -0.0227 1.0000 0.0160
-13.250 -1.0542 0.04959 0.04356 -0.0242 1.0000 0.0166
-13.000 -1.0564 0.04626 0.04009 -0.0253 1.0000 0.0172
-12.750 -1.0564 0.04329 0.03697 -0.0262 1.0000 0.0176
-12.500 -1.0610 0.04001 0.03361 -0.0271 1.0000 0.0181
-12.250 -1.0642 0.03710 0.03062 -0.0276 1.0000 0.0188
-12.000 -1.0640 0.03477 0.02818 -0.0275 1.0000 0.0194
-11.750 -1.0631 0.03275 0.02604 -0.0269 1.0000 0.0202
-11.500 -1.0616 0.03101 0.02419 -0.0256 1.0000 0.0210
-11.250 -1.0587 0.02956 0.02262 -0.0238 1.0000 0.0218
-11.000 -1.0533 0.02838 0.02130 -0.0216 1.0000 0.0229
-10.750 -1.0499 0.02695 0.01983 -0.0192 1.0000 0.0242
-10.500 -1.0392 0.02583 0.01864 -0.0176 1.0000 0.0259
-10.250 -1.0255 0.02484 0.01756 -0.0161 1.0000 0.0279
-10.000 -1.0109 0.02387 0.01648 -0.0147 1.0000 0.0301
-9.750 -0.9970 0.02278 0.01536 -0.0132 1.0000 0.0331
-9.500 -0.9798 0.02192 0.01439 -0.0120 1.0000 0.0366
-9.250 -0.9629 0.02097 0.01341 -0.0107 1.0000 0.0408
-9.000 -0.9442 0.02017 0.01255 -0.0096 1.0000 0.0466
-8.750 -0.9258 0.01932 0.01170 -0.0085 1.0000 0.0542
-8.500 -0.9062 0.01855 0.01092 -0.0074 1.0000 0.0633
-8.250 -0.8859 0.01784 0.01021 -0.0064 1.0000 0.0740
-8.000 -0.8654 0.01714 0.00953 -0.0055 1.0000 0.0875
-7.750 -0.8446 0.01648 0.00892 -0.0046 1.0000 0.1038
-7.250 -0.8018 0.01529 0.00786 -0.0028 1.0000 0.1436
-7.000 -0.7797 0.01479 0.00743 -0.0019 1.0000 0.1655
-6.750 -0.7574 0.01434 0.00703 -0.0011 1.0000 0.1867
-6.500 -0.7344 0.01397 0.00668 -0.0003 1.0000 0.2054
-6.250 -0.7112 0.01364 0.00635 0.0005 1.0000 0.2208
-6.000 -0.6879 0.01332 0.00605 0.0014 1.0000 0.2355
-5.750 -0.6646 0.01303 0.00576 0.0022 1.0000 0.2499
-5.250 -0.6180 0.01250 0.00526 0.0039 1.0000 0.2783
-5.000 -0.5949 0.01226 0.00505 0.0047 1.0000 0.2920
-4.750 -0.5718 0.01203 0.00484 0.0056 1.0000 0.3053
-4.500 -0.5353 0.01181 0.00463 0.0037 0.9883 0.3206
-4.250 -0.4978 0.01160 0.00444 0.0016 0.9712 0.3359
-4.000 -0.4606 0.01140 0.00424 -0.0003 0.9470 0.3507
-3.750 -0.4199 0.01122 0.00405 -0.0028 0.9202 0.3659
-3.500 -0.3801 0.01107 0.00387 -0.0051 0.8895 0.3806
-3.250 -0.3462 0.01096 0.00369 -0.0061 0.8563 0.3944
-3.000 -0.3170 0.01088 0.00355 -0.0061 0.8248 0.4074
-2.750 -0.2900 0.01084 0.00342 -0.0056 0.7958 0.4202
-2.500 -0.2638 0.01080 0.00330 -0.0050 0.7695 0.4330
-2.250 -0.2377 0.01078 0.00320 -0.0044 0.7451 0.4461
-2.000 -0.2115 0.01075 0.00311 -0.0038 0.7221 0.4593
-1.750 -0.1853 0.01073 0.00302 -0.0033 0.7006 0.4729
-1.500 -0.1590 0.01071 0.00295 -0.0028 0.6803 0.4866
-1.250 -0.1326 0.01069 0.00290 -0.0023 0.6608 0.5005
-1.000 -0.1062 0.01067 0.00285 -0.0018 0.6424 0.5147
-0.750 -0.0798 0.01066 0.00281 -0.0013 0.6246 0.5291
-0.500 -0.0532 0.01065 0.00279 -0.0009 0.6077 0.5440
-0.250 -0.0266 0.01065 0.00277 -0.0004 0.5909 0.5592
0.000 0.0000 0.01064 0.00277 0.0000 0.5749 0.5749
0.250 0.0266 0.01065 0.00277 0.0004 0.5591 0.5909
0.500 0.0532 0.01065 0.00279 0.0009 0.5440 0.6077
0.750 0.0797 0.01066 0.00281 0.0013 0.5290 0.6245
1.000 0.1062 0.01067 0.00285 0.0018 0.5146 0.6423
1.250 0.1326 0.01069 0.00290 0.0023 0.5005 0.6608
1.500 0.1589 0.01071 0.00295 0.0028 0.4866 0.6804
1.750 0.1853 0.01073 0.00302 0.0033 0.4729 0.7006
2.000 0.2115 0.01075 0.00311 0.0038 0.4593 0.7220
2.250 0.2376 0.01078 0.00320 0.0044 0.4460 0.7451
2.500 0.2637 0.01080 0.00330 0.0050 0.4330 0.7694
2.750 0.2900 0.01084 0.00342 0.0056 0.4202 0.7959
3.000 0.3169 0.01088 0.00355 0.0061 0.4074 0.8249
3.250 0.3462 0.01096 0.00369 0.0061 0.3944 0.8564
3.500 0.3801 0.01107 0.00387 0.0051 0.3806 0.8894
3.750 0.4199 0.01122 0.00405 0.0028 0.3659 0.9201
4.000 0.4606 0.01140 0.00424 0.0003 0.3507 0.9470
4.250 0.4978 0.01160 0.00444 -0.0016 0.3359 0.9711
4.500 0.5353 0.01181 0.00463 -0.0037 0.3206 0.9883
4.750 0.5718 0.01203 0.00484 -0.0056 0.3051 1.0000
5.000 0.5949 0.01226 0.00505 -0.0048 0.2919 1.0000
5.250 0.6181 0.01250 0.00526 -0.0039 0.2782 1.0000
5.750 0.6647 0.01303 0.00576 -0.0022 0.2499 1.0000
6.000 0.6880 0.01332 0.00605 -0.0014 0.2356 1.0000
6.250 0.7112 0.01364 0.00635 -0.0005 0.2208 1.0000
6.500 0.7344 0.01397 0.00668 0.0003 0.2053 1.0000
6.750 0.7575 0.01434 0.00703 0.0011 0.1868 1.0000
7.000 0.7798 0.01479 0.00741 0.0019 0.1655 1.0000
7.250 0.8018 0.01529 0.00786 0.0028 0.1435 1.0000
7.750 0.8446 0.01648 0.00892 0.0046 0.1039 1.0000
8.000 0.8654 0.01715 0.00953 0.0055 0.0873 1.0000
8.250 0.8859 0.01784 0.01021 0.0065 0.0739 1.0000
8.500 0.9061 0.01855 0.01092 0.0074 0.0633 1.0000
8.750 0.9257 0.01931 0.01170 0.0085 0.0541 1.0000
9.000 0.9441 0.02017 0.01255 0.0096 0.0466 1.0000
9.250 0.9629 0.02097 0.01340 0.0107 0.0409 1.0000
9.500 0.9797 0.02191 0.01439 0.0120 0.0367 1.0000
9.750 0.9968 0.02277 0.01536 0.0133 0.0332 1.0000
10.000 1.0108 0.02387 0.01648 0.0147 0.0301 1.0000
10.250 1.0254 0.02483 0.01755 0.0161 0.0279 1.0000
10.500 1.0388 0.02584 0.01866 0.0176 0.0260 1.0000
10.750 1.0495 0.02696 0.01984 0.0193 0.0241 1.0000
11.000 1.0532 0.02837 0.02129 0.0216 0.0229 1.0000
11.250 1.0588 0.02954 0.02260 0.0238 0.0218 1.0000
11.500 1.0615 0.03101 0.02419 0.0257 0.0209 1.0000
11.750 1.0632 0.03273 0.02602 0.0269 0.0201 1.0000
12.000 1.0645 0.03472 0.02814 0.0275 0.0193 1.0000
12.250 1.0642 0.03710 0.03061 0.0276 0.0187 1.0000
12.500 1.0617 0.03994 0.03354 0.0271 0.0182 1.0000
12.750 1.0566 0.04327 0.03694 0.0263 0.0176 1.0000
13.000 1.0572 0.04618 0.04001 0.0253 0.0171 1.0000
13.250 1.0551 0.04950 0.04348 0.0242 0.0165 1.0000
13.500 1.0511 0.05316 0.04727 0.0228 0.0161 1.0000
13.750 1.0473 0.05695 0.05118 0.0211 0.0155 1.0000
14.000 1.0417 0.06104 0.05538 0.0192 0.0151 1.0000
14.250 1.0359 0.06522 0.05967 0.0173 0.0149 1.0000
14.500 1.0292 0.06967 0.06423 0.0151 0.0146 1.0000
14.750 1.0216 0.07433 0.06899 0.0129 0.0144 1.0000
15.000 1.0130 0.07930 0.07405 0.0103 0.0142 1.0000
15.250 1.0057 0.08426 0.07911 0.0078 0.0140 1.0000
15.500 0.9974 0.08952 0.08446 0.0051 0.0138 1.0000
15.750 0.9892 0.09483 0.08985 0.0024 0.0136 1.0000
16.000 0.9803 0.10049 0.09562 -0.0005 0.0135 1.0000
16.250 0.9695 0.10688 0.10217 -0.0040 0.0134 1.0000
16.500 0.9584 0.11346 0.10889 -0.0077 0.0133 1.0000
16.750 0.9457 0.12061 0.11618 -0.0116 0.0133 1.0000
17.000 0.9300 0.12870 0.12442 -0.0163 0.0132 1.0000
17.250 0.9136 0.13727 0.13314 -0.0212 0.0132 1.0000
17.500 0.8896 0.14828 0.14431 -0.0275 0.0133 1.0000
17.750 0.8494 0.16478 0.16098 -0.0365 0.0134 1.0000
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Polar data table (+)
Polar graphs
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