EPPLER 715 AIRFOIL (e715-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 715 AIRFOIL (e715-il) Reynolds number: 200,000 Max Cl/Cd: 74.88 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e715-il-200000-n5.txt Download as CSV file: xf-e715-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 715 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-14.250 -0.6437 0.10696 0.10333 -0.0116 1.0000 0.0097
-14.000 -0.6760 0.09456 0.09076 -0.0190 1.0000 0.0096
-13.750 -0.6936 0.08630 0.08240 -0.0243 1.0000 0.0094
-13.500 -0.7148 0.07794 0.07390 -0.0297 1.0000 0.0093
-13.250 -0.7319 0.07095 0.06673 -0.0345 1.0000 0.0094
-13.000 -0.7466 0.06496 0.06060 -0.0383 1.0000 0.0093
-12.750 -0.7589 0.05959 0.05505 -0.0419 1.0000 0.0094
-12.500 -0.7694 0.05481 0.05013 -0.0446 1.0000 0.0094
-12.250 -0.7699 0.05021 0.04519 -0.0494 0.8603 0.0094
-12.000 -0.7746 0.04669 0.04125 -0.0512 0.8046 0.0097
-11.750 -0.7785 0.04346 0.03771 -0.0524 0.7760 0.0097
-11.500 -0.7800 0.04061 0.03465 -0.0535 0.7554 0.0099
-11.000 -0.7802 0.03598 0.02971 -0.0549 0.7252 0.0105
-10.750 -0.7794 0.03423 0.02779 -0.0542 0.7136 0.0108
-10.500 -0.7754 0.03281 0.02619 -0.0529 0.7037 0.0111
-10.250 -0.7666 0.03126 0.02443 -0.0519 0.6946 0.0116
-10.000 -0.7552 0.02977 0.02273 -0.0510 0.6865 0.0120
-9.750 -0.7420 0.02837 0.02111 -0.0501 0.6790 0.0125
-9.500 -0.7277 0.02702 0.01961 -0.0492 0.6721 0.0129
-9.250 -0.7118 0.02583 0.01830 -0.0485 0.6656 0.0135
-9.000 -0.6938 0.02480 0.01713 -0.0479 0.6603 0.0142
-8.750 -0.6746 0.02377 0.01596 -0.0472 0.6547 0.0152
-8.500 -0.6550 0.02276 0.01480 -0.0466 0.6497 0.0165
-8.250 -0.6338 0.02199 0.01392 -0.0462 0.6455 0.0182
-8.000 -0.6115 0.02120 0.01300 -0.0458 0.6405 0.0207
-7.750 -0.5891 0.02044 0.01217 -0.0454 0.6358 0.0235
-7.500 -0.5664 0.01969 0.01131 -0.0449 0.6318 0.0270
-7.250 -0.5424 0.01909 0.01061 -0.0446 0.6278 0.0318
-7.000 -0.5185 0.01842 0.00990 -0.0444 0.6238 0.0380
-6.750 -0.4942 0.01780 0.00923 -0.0441 0.6202 0.0459
-6.500 -0.4696 0.01723 0.00863 -0.0438 0.6170 0.0563
-6.250 -0.4445 0.01672 0.00807 -0.0436 0.6142 0.0699
-6.000 -0.4193 0.01616 0.00757 -0.0435 0.6107 0.0881
-5.750 -0.3939 0.01565 0.00710 -0.0433 0.6072 0.1120
-5.500 -0.3684 0.01514 0.00667 -0.0432 0.6039 0.1418
-5.250 -0.3428 0.01467 0.00627 -0.0431 0.6011 0.1765
-5.000 -0.3170 0.01425 0.00592 -0.0430 0.5987 0.2141
-4.750 -0.2908 0.01383 0.00563 -0.0429 0.5958 0.2554
-4.500 -0.2646 0.01347 0.00541 -0.0428 0.5929 0.3007
-4.250 -0.2380 0.01323 0.00530 -0.0426 0.5902 0.3456
-4.000 -0.2107 0.01315 0.00526 -0.0425 0.5875 0.3814
-3.750 -0.1829 0.01315 0.00522 -0.0423 0.5850 0.4077
-3.500 -0.1548 0.01321 0.00520 -0.0423 0.5827 0.4271
-3.250 -0.1263 0.01326 0.00521 -0.0423 0.5801 0.4427
-3.000 -0.0977 0.01332 0.00518 -0.0423 0.5775 0.4561
-2.750 -0.0693 0.01338 0.00518 -0.0423 0.5751 0.4673
-2.500 -0.0409 0.01343 0.00516 -0.0422 0.5726 0.4763
-2.250 -0.0123 0.01349 0.00508 -0.0423 0.5704 0.4856
-2.000 0.0159 0.01352 0.00507 -0.0422 0.5684 0.4922
-1.750 0.0446 0.01358 0.00505 -0.0423 0.5661 0.5004
-1.500 0.0730 0.01360 0.00508 -0.0424 0.5637 0.5065
-1.250 0.1016 0.01364 0.00508 -0.0425 0.5613 0.5130
-1.000 0.1301 0.01366 0.00505 -0.0426 0.5588 0.5187
-0.750 0.1585 0.01367 0.00504 -0.0426 0.5565 0.5237
-0.500 0.1870 0.01371 0.00501 -0.0427 0.5545 0.5295
-0.250 0.2155 0.01376 0.00500 -0.0427 0.5529 0.5345
0.000 0.2439 0.01379 0.00506 -0.0428 0.5507 0.5392
0.250 0.2724 0.01383 0.00512 -0.0430 0.5481 0.5441
0.500 0.3010 0.01388 0.00515 -0.0431 0.5455 0.5485
0.750 0.3293 0.01389 0.00520 -0.0432 0.5432 0.5523
1.000 0.3577 0.01394 0.00524 -0.0433 0.5412 0.5564
1.250 0.3863 0.01399 0.00527 -0.0434 0.5392 0.5608
1.500 0.4147 0.01405 0.00530 -0.0435 0.5374 0.5647
1.750 0.4428 0.01410 0.00544 -0.0437 0.5348 0.5685
2.000 0.4709 0.01418 0.00558 -0.0438 0.5322 0.5729
2.250 0.4992 0.01426 0.00570 -0.0439 0.5296 0.5775
2.500 0.5273 0.01431 0.00579 -0.0440 0.5271 0.5813
2.750 0.5554 0.01436 0.00589 -0.0441 0.5249 0.5858
3.000 0.5837 0.01443 0.00596 -0.0441 0.5229 0.5909
3.250 0.6117 0.01452 0.00612 -0.0442 0.5204 0.5957
3.500 0.6391 0.01461 0.00635 -0.0443 0.5171 0.6006
3.750 0.6668 0.01469 0.00651 -0.0443 0.5138 0.6066
4.000 0.6946 0.01473 0.00663 -0.0443 0.5108 0.6128
4.250 0.7225 0.01475 0.00670 -0.0443 0.5081 0.6198
4.500 0.7500 0.01482 0.00687 -0.0443 0.5048 0.6273
4.750 0.7768 0.01489 0.00711 -0.0442 0.5003 0.6366
5.000 0.8040 0.01490 0.00724 -0.0441 0.4963 0.6483
5.250 0.8315 0.01485 0.00728 -0.0440 0.4927 0.6635
5.500 0.8576 0.01487 0.00750 -0.0438 0.4880 0.6852
5.750 0.8835 0.01480 0.00769 -0.0434 0.4826 0.7236
6.000 0.9287 0.01430 0.00769 -0.0466 0.4774 1.0000
6.250 0.9548 0.01445 0.00795 -0.0465 0.4710 1.0000
6.500 0.9814 0.01452 0.00807 -0.0463 0.4648 1.0000
6.750 1.0077 0.01461 0.00823 -0.0461 0.4580 1.0000
7.000 1.0337 0.01469 0.00837 -0.0459 0.4498 1.0000
7.250 1.0593 0.01481 0.00858 -0.0456 0.4403 1.0000
7.500 1.0849 0.01490 0.00871 -0.0452 0.4304 1.0000
7.750 1.1098 0.01502 0.00888 -0.0448 0.4182 1.0000
8.000 1.1338 0.01520 0.00910 -0.0443 0.4030 1.0000
8.250 1.1569 0.01545 0.00939 -0.0437 0.3835 1.0000
8.500 1.1777 0.01582 0.00968 -0.0428 0.3592 1.0000
8.750 1.1955 0.01640 0.01015 -0.0416 0.3295 1.0000
9.000 1.2092 0.01723 0.01083 -0.0401 0.2973 1.0000
9.250 1.2192 0.01827 0.01174 -0.0382 0.2669 1.0000
9.500 1.2258 0.01943 0.01278 -0.0359 0.2406 1.0000
9.750 1.2292 0.02065 0.01392 -0.0334 0.2183 1.0000
10.000 1.2253 0.02204 0.01526 -0.0302 0.2008 1.0000
10.250 1.2211 0.02384 0.01702 -0.0280 0.1851 1.0000
10.500 1.2185 0.02591 0.01905 -0.0266 0.1697 1.0000
10.750 1.2168 0.02811 0.02123 -0.0256 0.1555 1.0000
11.000 1.2150 0.03045 0.02353 -0.0247 0.1417 1.0000
11.250 1.2140 0.03278 0.02584 -0.0240 0.1293 1.0000
11.500 1.2139 0.03508 0.02813 -0.0234 0.1177 1.0000
11.750 1.2140 0.03739 0.03044 -0.0228 0.1072 1.0000
12.000 1.2140 0.03975 0.03279 -0.0223 0.0979 1.0000
12.250 1.2127 0.04227 0.03529 -0.0219 0.0893 1.0000
12.500 1.2147 0.04452 0.03757 -0.0215 0.0813 1.0000
12.750 1.2150 0.04697 0.04003 -0.0212 0.0744 1.0000
13.000 1.2156 0.04943 0.04251 -0.0210 0.0678 1.0000
13.250 1.2169 0.05192 0.04503 -0.0208 0.0621 1.0000
13.500 1.2177 0.05457 0.04770 -0.0208 0.0566 1.0000
13.750 1.2195 0.05718 0.05035 -0.0209 0.0518 1.0000
14.000 1.2205 0.05995 0.05317 -0.0211 0.0472 1.0000
14.250 1.2212 0.06281 0.05607 -0.0213 0.0437 1.0000
14.500 1.2234 0.06557 0.05890 -0.0216 0.0402 1.0000
14.750 1.2225 0.06877 0.06214 -0.0221 0.0373 1.0000
15.000 1.2238 0.07176 0.06521 -0.0226 0.0346 1.0000
15.250 1.2246 0.07487 0.06840 -0.0232 0.0319 1.0000
15.500 1.2227 0.07843 0.07199 -0.0240 0.0298 1.0000
15.750 1.2229 0.08177 0.07543 -0.0248 0.0279 1.0000
16.000 1.2231 0.08516 0.07892 -0.0256 0.0261 1.0000
16.250 1.2212 0.08893 0.08276 -0.0267 0.0244 1.0000
16.500 1.2175 0.09305 0.08693 -0.0280 0.0230 1.0000
16.750 1.2175 0.09667 0.09070 -0.0291 0.0215 1.0000
17.000 1.2157 0.10062 0.09476 -0.0305 0.0204 1.0000
17.250 1.2119 0.10498 0.09920 -0.0321 0.0193 1.0000
17.500 1.2064 0.10970 0.10399 -0.0340 0.0185 1.0000
17.750 1.2045 0.11387 0.10828 -0.0356 0.0176 1.0000
18.000 1.2020 0.11820 0.11274 -0.0374 0.0166 1.0000
18.250 1.1981 0.12284 0.11749 -0.0395 0.0158 1.0000
18.500 1.1931 0.12777 0.12251 -0.0419 0.0151 1.0000
18.750 1.1874 0.13289 0.12770 -0.0444 0.0146 1.0000
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Polar data table (+)
Polar graphs
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