EPPLER 327 AIRFOIL (e327-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 327 AIRFOIL (e327-il) Reynolds number: 1,000,000 Max Cl/Cd: 98.3 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e327-il-1000000-n5.txt Download as CSV file: xf-e327-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 327 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4904 0.08003 0.07846 -0.0277 1.0000 0.0038
-9.750 -0.5091 0.07156 0.06995 -0.0359 0.9693 0.0038
-9.500 -0.5212 0.05843 0.05627 -0.0497 0.8569 0.0041
-9.250 -0.5501 0.05439 0.05190 -0.0445 0.7972 0.0043
-9.000 -0.5647 0.05177 0.04906 -0.0405 0.7640 0.0042
-8.750 -0.5818 0.04666 0.04368 -0.0363 0.7412 0.0042
-8.500 -0.5919 0.04188 0.03862 -0.0323 0.7240 0.0042
-8.250 -0.6351 0.02828 0.02416 -0.0228 0.7173 0.0041
-8.000 -0.6305 0.02461 0.02000 -0.0193 0.7008 0.0041
-7.750 -0.6164 0.02262 0.01766 -0.0171 0.6830 0.0042
-7.500 -0.5989 0.02105 0.01579 -0.0154 0.6665 0.0042
-7.250 -0.5779 0.02021 0.01475 -0.0143 0.6512 0.0043
-7.000 -0.5574 0.01899 0.01328 -0.0130 0.6371 0.0043
-6.750 -0.5353 0.01806 0.01213 -0.0120 0.6227 0.0043
-6.500 -0.5130 0.01694 0.01081 -0.0110 0.6099 0.0043
-6.250 -0.4895 0.01609 0.00979 -0.0102 0.5982 0.0043
-6.000 -0.4657 0.01533 0.00888 -0.0095 0.5865 0.0043
-5.750 -0.4422 0.01446 0.00785 -0.0086 0.5749 0.0043
-5.500 -0.4185 0.01380 0.00708 -0.0078 0.5626 0.0043
-5.250 -0.3943 0.01333 0.00652 -0.0071 0.5527 0.0043
-5.000 -0.3709 0.01280 0.00589 -0.0062 0.5427 0.0044
-4.750 -0.3478 0.01228 0.00528 -0.0053 0.5319 0.0044
-4.500 -0.3245 0.01183 0.00476 -0.0044 0.5227 0.0045
-4.250 -0.3006 0.01152 0.00437 -0.0036 0.5127 0.0045
-4.000 -0.2765 0.01119 0.00399 -0.0028 0.5045 0.0046
-3.750 -0.2524 0.01091 0.00364 -0.0021 0.4956 0.0048
-3.500 -0.2274 0.01070 0.00339 -0.0015 0.4867 0.0049
-3.250 -0.2024 0.01051 0.00315 -0.0009 0.4783 0.0050
-3.000 -0.1771 0.01034 0.00294 -0.0003 0.4706 0.0052
-2.750 -0.1518 0.01018 0.00272 0.0002 0.4634 0.0058
-2.500 -0.1261 0.01004 0.00255 0.0007 0.4555 0.0062
-2.250 -0.1008 0.00990 0.00237 0.0012 0.4480 0.0080
-2.000 -0.0749 0.00977 0.00223 0.0016 0.4411 0.0106
-1.500 -0.0239 0.00949 0.00201 0.0026 0.4284 0.0364
-1.250 0.0014 0.00935 0.00192 0.0030 0.4213 0.0587
-1.000 0.0229 0.00891 0.00181 0.0041 0.4158 0.1607
-0.750 0.0103 0.00635 0.00136 0.0113 0.4124 0.7434
-0.500 0.0351 0.00636 0.00147 0.0122 0.4066 0.8010
-0.250 0.0625 0.00643 0.00151 0.0124 0.4011 0.8136
0.000 0.0899 0.00652 0.00157 0.0126 0.3952 0.8261
0.250 0.1172 0.00663 0.00162 0.0128 0.3894 0.8355
0.500 0.1449 0.00670 0.00168 0.0130 0.3849 0.8415
0.750 0.1727 0.00679 0.00173 0.0131 0.3798 0.8466
1.000 0.2009 0.00685 0.00173 0.0130 0.3742 0.8481
1.250 0.2292 0.00690 0.00174 0.0128 0.3697 0.8490
1.500 0.2576 0.00695 0.00174 0.0127 0.3651 0.8501
1.750 0.2858 0.00701 0.00176 0.0125 0.3597 0.8511
2.000 0.3140 0.00708 0.00178 0.0124 0.3552 0.8519
2.250 0.3424 0.00713 0.00180 0.0122 0.3511 0.8527
2.500 0.3705 0.00718 0.00183 0.0121 0.3462 0.8536
2.750 0.3984 0.00726 0.00187 0.0120 0.3413 0.8545
3.000 0.4266 0.00731 0.00192 0.0119 0.3376 0.8554
3.250 0.4546 0.00737 0.00197 0.0117 0.3330 0.8564
3.500 0.4824 0.00746 0.00203 0.0117 0.3280 0.8575
3.750 0.5103 0.00754 0.00210 0.0115 0.3241 0.8585
4.000 0.5382 0.00761 0.00216 0.0114 0.3195 0.8594
4.250 0.5659 0.00771 0.00224 0.0113 0.3146 0.8604
4.500 0.5935 0.00780 0.00233 0.0112 0.3101 0.8614
4.750 0.6213 0.00788 0.00241 0.0111 0.3054 0.8625
5.000 0.6488 0.00799 0.00250 0.0110 0.3000 0.8635
5.250 0.6761 0.00810 0.00261 0.0109 0.2950 0.8645
5.500 0.7037 0.00820 0.00270 0.0108 0.2896 0.8656
5.750 0.7307 0.00834 0.00282 0.0108 0.2832 0.8666
6.000 0.7579 0.00845 0.00294 0.0107 0.2779 0.8676
6.250 0.7849 0.00858 0.00306 0.0107 0.2714 0.8687
6.500 0.8114 0.00872 0.00320 0.0107 0.2650 0.8700
6.750 0.8379 0.00886 0.00335 0.0108 0.2575 0.8713
7.000 0.8640 0.00903 0.00352 0.0109 0.2505 0.8725
7.250 0.8901 0.00920 0.00369 0.0110 0.2423 0.8737
7.500 0.9158 0.00939 0.00387 0.0111 0.2339 0.8751
7.750 0.9409 0.00963 0.00408 0.0113 0.2241 0.8765
8.000 0.9663 0.00983 0.00429 0.0115 0.2147 0.8779
8.250 0.9909 0.01009 0.00453 0.0118 0.2042 0.8794
8.500 1.0149 0.01039 0.00479 0.0121 0.1923 0.8809
8.750 1.0385 0.01070 0.00507 0.0125 0.1810 0.8824
9.000 1.0613 0.01106 0.00539 0.0131 0.1680 0.8839
9.250 1.0830 0.01145 0.00574 0.0137 0.1539 0.8856
9.500 1.1040 0.01186 0.00612 0.0146 0.1400 0.8876
9.750 1.1237 0.01233 0.00655 0.0155 0.1252 0.8899
10.000 1.1429 0.01281 0.00699 0.0166 0.1121 0.8924
10.250 1.1613 0.01331 0.00745 0.0178 0.0998 0.8951
10.500 1.1795 0.01380 0.00792 0.0189 0.0900 0.8977
11.000 1.2119 0.01482 0.00893 0.0219 0.0719 0.9034
11.250 1.2266 0.01530 0.00942 0.0237 0.0657 0.9071
11.500 1.2353 0.01586 0.00998 0.0265 0.0587 0.9120
11.750 1.2450 0.01639 0.01054 0.0291 0.0533 0.9171
12.000 1.2515 0.01703 0.01122 0.0320 0.0479 0.9242
12.250 1.2580 0.01770 0.01193 0.0347 0.0434 0.9326
12.750 1.2746 0.01942 0.01379 0.0383 0.0353 0.9642
13.000 1.2949 0.02097 0.01535 0.0361 0.0282 0.9888
13.250 1.3024 0.02216 0.01660 0.0372 0.0265 1.0000
13.500 1.3012 0.02404 0.01848 0.0384 0.0219 1.0000
13.750 1.3055 0.02570 0.02020 0.0391 0.0205 1.0000
14.000 1.3096 0.02751 0.02208 0.0394 0.0197 1.0000
14.250 1.3047 0.03025 0.02484 0.0397 0.0158 1.0000
14.500 1.3074 0.03242 0.02709 0.0396 0.0156 1.0000
14.750 1.3027 0.03541 0.03012 0.0394 0.0133 1.0000
15.000 1.3014 0.03812 0.03292 0.0391 0.0127 1.0000
15.250 1.2976 0.04117 0.03603 0.0386 0.0119 1.0000
15.500 1.2896 0.04472 0.03964 0.0380 0.0101 1.0000
15.750 1.2878 0.04764 0.04266 0.0374 0.0106 1.0000
16.000 1.2828 0.05095 0.04605 0.0367 0.0102 1.0000
16.250 1.2766 0.05454 0.04973 0.0358 0.0099 1.0000
16.500 1.2667 0.05867 0.05393 0.0346 0.0090 1.0000
16.750 1.2612 0.06237 0.05771 0.0334 0.0086 1.0000
17.000 1.2548 0.06625 0.06166 0.0322 0.0082 1.0000
17.250 1.2483 0.07024 0.06573 0.0308 0.0078 1.0000
17.500 1.2417 0.07431 0.06988 0.0293 0.0076 1.0000
17.750 1.2312 0.07899 0.07463 0.0276 0.0066 1.0000
18.000 1.2247 0.08320 0.07891 0.0259 0.0061 1.0000
18.250 1.2201 0.08721 0.08302 0.0243 0.0065 1.0000
18.500 1.2129 0.09167 0.08755 0.0224 0.0061 1.0000
18.750 1.2046 0.09639 0.09234 0.0204 0.0055 1.0000
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