EPPLER 393 AIRFOIL (e393-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 393 AIRFOIL (e393-il) Reynolds number: 100,000 Max Cl/Cd: 61.98 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e393-il-100000-n5.txt Download as CSV file: xf-e393-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 393 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3338 0.09071 0.08610 -0.0464 1.0000 0.0239
-8.500 -0.3432 0.08739 0.08289 -0.0463 1.0000 0.0237
-8.000 -0.3718 0.07766 0.07337 -0.0494 0.9963 0.0221
-7.750 -0.3606 0.07090 0.06662 -0.0580 0.9852 0.0219
-7.500 -0.3474 0.05882 0.05435 -0.0760 0.9704 0.0220
-7.250 -0.3347 0.05067 0.04578 -0.0869 0.9566 0.0221
-6.750 -0.2964 0.04177 0.03636 -0.0961 0.9343 0.0240
-6.500 -0.2697 0.03678 0.03078 -0.1006 0.9261 0.0243
-6.250 -0.2410 0.03271 0.02610 -0.1036 0.9178 0.0247
-6.000 -0.2119 0.02959 0.02244 -0.1055 0.9092 0.0255
-5.750 -0.1786 0.02691 0.01927 -0.1075 0.9028 0.0267
-5.500 -0.1484 0.02480 0.01676 -0.1084 0.8940 0.0282
-5.250 -0.1139 0.02305 0.01466 -0.1100 0.8878 0.0319
-5.000 -0.0848 0.02188 0.01339 -0.1106 0.8783 0.0357
-4.750 -0.0516 0.02056 0.01185 -0.1116 0.8714 0.0398
-4.500 -0.0218 0.01958 0.01082 -0.1123 0.8622 0.0472
-4.250 0.0087 0.01863 0.00974 -0.1129 0.8537 0.0557
-4.000 0.0406 0.01780 0.00887 -0.1139 0.8459 0.0709
-3.750 0.0699 0.01705 0.00809 -0.1144 0.8365 0.0953
-3.500 0.1013 0.01626 0.00746 -0.1155 0.8290 0.1485
-3.250 0.1297 0.01549 0.00706 -0.1162 0.8199 0.2432
-3.000 0.1581 0.01488 0.00688 -0.1167 0.8116 0.3702
-2.750 0.1869 0.01464 0.00679 -0.1168 0.8037 0.4585
-2.500 0.2140 0.01458 0.00671 -0.1164 0.7951 0.5161
-2.250 0.2429 0.01451 0.00660 -0.1163 0.7880 0.5601
-2.000 0.2691 0.01452 0.00656 -0.1158 0.7793 0.5949
-1.750 0.2974 0.01449 0.00645 -0.1155 0.7727 0.6267
-1.500 0.3229 0.01450 0.00643 -0.1148 0.7643 0.6544
-1.250 0.3499 0.01448 0.00635 -0.1143 0.7578 0.6806
-1.000 0.3752 0.01450 0.00636 -0.1136 0.7499 0.7056
-0.750 0.4020 0.01450 0.00628 -0.1131 0.7438 0.7308
-0.500 0.4263 0.01452 0.00631 -0.1122 0.7361 0.7551
0.000 0.4753 0.01454 0.00629 -0.1103 0.7229 0.8051
0.250 0.4999 0.01452 0.00624 -0.1093 0.7172 0.8331
0.500 0.5220 0.01452 0.00627 -0.1079 0.7102 0.8660
0.750 0.5481 0.01447 0.00621 -0.1073 0.7043 0.9094
1.000 0.5840 0.01444 0.00616 -0.1090 0.6979 1.0000
1.250 0.6134 0.01462 0.00624 -0.1097 0.6915 1.0000
1.500 0.6432 0.01480 0.00631 -0.1103 0.6859 1.0000
1.750 0.6708 0.01502 0.00651 -0.1106 0.6790 1.0000
2.000 0.7006 0.01519 0.00659 -0.1111 0.6739 1.0000
2.250 0.7271 0.01544 0.00684 -0.1111 0.6668 1.0000
2.500 0.7557 0.01564 0.00699 -0.1114 0.6612 1.0000
2.750 0.7828 0.01589 0.00726 -0.1115 0.6548 1.0000
3.000 0.8102 0.01612 0.00749 -0.1115 0.6485 1.0000
3.250 0.8381 0.01634 0.00770 -0.1116 0.6426 1.0000
3.500 0.8642 0.01661 0.00801 -0.1115 0.6356 1.0000
3.750 0.8927 0.01680 0.00822 -0.1116 0.6298 1.0000
4.000 0.9176 0.01709 0.00859 -0.1113 0.6217 1.0000
4.250 0.9455 0.01727 0.00878 -0.1113 0.6150 1.0000
4.500 0.9703 0.01753 0.00912 -0.1108 0.6062 1.0000
4.750 0.9964 0.01774 0.00943 -0.1105 0.5980 1.0000
5.000 1.0227 0.01792 0.00967 -0.1102 0.5894 1.0000
5.250 1.0469 0.01817 0.01002 -0.1096 0.5792 1.0000
5.500 1.0721 0.01835 0.01028 -0.1091 0.5691 1.0000
5.750 1.0979 0.01849 0.01051 -0.1086 0.5588 1.0000
6.000 1.1214 0.01869 0.01082 -0.1078 0.5464 1.0000
6.250 1.1445 0.01889 0.01113 -0.1069 0.5330 1.0000
6.500 1.1673 0.01909 0.01144 -0.1060 0.5186 1.0000
6.750 1.1899 0.01929 0.01173 -0.1049 0.5030 1.0000
7.000 1.2105 0.01957 0.01217 -0.1036 0.4844 1.0000
7.250 1.2304 0.01985 0.01253 -0.1022 0.4634 1.0000
7.500 1.2490 0.02020 0.01296 -0.1006 0.4388 1.0000
7.750 1.2659 0.02064 0.01342 -0.0987 0.4098 1.0000
8.000 1.2801 0.02123 0.01395 -0.0965 0.3743 1.0000
8.250 1.2902 0.02207 0.01463 -0.0938 0.3321 1.0000
8.500 1.2961 0.02318 0.01558 -0.0906 0.2892 1.0000
8.750 1.2978 0.02446 0.01666 -0.0870 0.2514 1.0000
9.000 1.2989 0.02586 0.01792 -0.0835 0.2186 1.0000
9.250 1.2994 0.02739 0.01933 -0.0803 0.1887 1.0000
9.500 1.3000 0.02904 0.02088 -0.0774 0.1635 1.0000
9.750 1.3003 0.03083 0.02259 -0.0747 0.1410 1.0000
10.000 1.3015 0.03268 0.02441 -0.0724 0.1209 1.0000
10.250 1.3014 0.03476 0.02643 -0.0703 0.1029 1.0000
10.500 1.3014 0.03696 0.02858 -0.0685 0.0858 1.0000
10.750 1.3018 0.03925 0.03083 -0.0669 0.0695 1.0000
11.000 1.3017 0.04171 0.03325 -0.0656 0.0560 1.0000
11.250 1.3015 0.04429 0.03588 -0.0644 0.0456 1.0000
11.500 1.3003 0.04708 0.03870 -0.0633 0.0378 1.0000
11.750 1.2975 0.05016 0.04180 -0.0624 0.0323 1.0000
12.000 1.2968 0.05311 0.04489 -0.0617 0.0279 1.0000
12.250 1.2949 0.05628 0.04815 -0.0612 0.0246 1.0000
12.500 1.2900 0.05990 0.05185 -0.0608 0.0224 1.0000
12.750 1.2888 0.06321 0.05537 -0.0605 0.0207 1.0000
13.000 1.2871 0.06667 0.05899 -0.0604 0.0194 1.0000
13.250 1.2853 0.07022 0.06270 -0.0604 0.0184 1.0000
13.500 1.2833 0.07390 0.06652 -0.0606 0.0176 1.0000
13.750 1.2805 0.07777 0.07052 -0.0610 0.0169 1.0000
14.000 1.2773 0.08180 0.07467 -0.0613 0.0163 1.0000
14.250 1.2767 0.08558 0.07859 -0.0616 0.0158 1.0000
14.500 1.2773 0.08934 0.08257 -0.0620 0.0154 1.0000
14.750 1.2766 0.09338 0.08685 -0.0626 0.0149 1.0000
15.000 1.2741 0.09780 0.09149 -0.0637 0.0145 1.0000
15.250 1.2701 0.10257 0.09650 -0.0651 0.0141 1.0000
15.500 1.2644 0.10774 0.10189 -0.0671 0.0137 1.0000
15.750 1.2576 0.11327 0.10768 -0.0695 0.0134 1.0000
16.000 1.2496 0.11914 0.11376 -0.0723 0.0131 1.0000
16.250 1.2406 0.12546 0.12029 -0.0756 0.0129 1.0000
16.500 1.2305 0.13222 0.12725 -0.0794 0.0128 1.0000
16.750 1.2190 0.13966 0.13490 -0.0839 0.0127 1.0000
17.000 1.2052 0.14808 0.14354 -0.0891 0.0128 1.0000
17.250 1.1884 0.15786 0.15353 -0.0955 0.0129 1.0000
17.500 1.1649 0.17067 0.16651 -0.1040 0.0136 1.0000
17.750 1.1377 0.18642 0.18240 -0.1140 0.0144 1.0000
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Polar data table (+)
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