EPPLER 360 AIRFOIL (e360-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 360 AIRFOIL (e360-il) Reynolds number: 500,000 Max Cl/Cd: 69.05 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e360-il-500000-n5.txt Download as CSV file: xf-e360-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 360 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.6674 0.06599 0.06346 -0.0392 1.0000 0.0062
-11.500 -0.7022 0.05534 0.05253 -0.0469 1.0000 0.0061
-11.250 -0.7318 0.04939 0.04642 -0.0487 1.0000 0.0060
-11.000 -0.7533 0.04540 0.04227 -0.0480 1.0000 0.0059
-10.750 -0.7766 0.04140 0.03799 -0.0454 1.0000 0.0060
-10.500 -0.7930 0.03862 0.03501 -0.0417 1.0000 0.0059
-10.250 -0.8123 0.03569 0.03177 -0.0363 1.0000 0.0060
-10.000 -0.8170 0.03336 0.02919 -0.0326 1.0000 0.0060
-9.750 -0.8154 0.03145 0.02704 -0.0293 1.0000 0.0060
-9.500 -0.8137 0.02932 0.02463 -0.0259 1.0000 0.0061
-9.250 -0.8083 0.02743 0.02248 -0.0228 1.0000 0.0061
-9.000 -0.7995 0.02586 0.02069 -0.0200 1.0000 0.0061
-8.750 -0.7889 0.02442 0.01905 -0.0174 1.0000 0.0061
-8.500 -0.7631 0.02279 0.01719 -0.0179 0.9954 0.0061
-8.250 -0.7365 0.02111 0.01531 -0.0184 0.9881 0.0061
-8.000 -0.7089 0.01974 0.01377 -0.0190 0.9794 0.0062
-7.750 -0.6803 0.01849 0.01237 -0.0198 0.9675 0.0063
-7.500 -0.6473 0.01739 0.01117 -0.0213 0.9507 0.0064
-7.250 -0.6084 0.01636 0.01004 -0.0241 0.9311 0.0065
-7.000 -0.5732 0.01554 0.00909 -0.0259 0.9043 0.0066
-6.750 -0.5472 0.01497 0.00837 -0.0257 0.8757 0.0069
-6.250 -0.5027 0.01406 0.00718 -0.0235 0.8289 0.0072
-6.000 -0.4804 0.01364 0.00664 -0.0224 0.8098 0.0075
-5.750 -0.4578 0.01324 0.00612 -0.0214 0.7935 0.0079
-5.500 -0.4346 0.01290 0.00568 -0.0204 0.7786 0.0082
-5.250 -0.4116 0.01252 0.00521 -0.0195 0.7648 0.0088
-5.000 -0.3878 0.01222 0.00483 -0.0187 0.7518 0.0094
-4.750 -0.3635 0.01195 0.00449 -0.0179 0.7397 0.0104
-4.500 -0.3393 0.01166 0.00414 -0.0172 0.7282 0.0120
-4.250 -0.3146 0.01143 0.00385 -0.0166 0.7174 0.0142
-4.000 -0.2902 0.01117 0.00357 -0.0159 0.7069 0.0197
-3.750 -0.2656 0.01089 0.00333 -0.0153 0.6974 0.0305
-3.500 -0.2410 0.01065 0.00311 -0.0146 0.6883 0.0459
-3.250 -0.2161 0.01040 0.00291 -0.0141 0.6791 0.0639
-3.000 -0.1919 0.01012 0.00272 -0.0135 0.6711 0.0960
-2.750 -0.1689 0.00968 0.00251 -0.0127 0.6629 0.1583
-2.500 -0.1479 0.00910 0.00229 -0.0116 0.6555 0.2606
-2.250 -0.1279 0.00845 0.00207 -0.0104 0.6479 0.3823
-2.000 -0.1090 0.00781 0.00187 -0.0088 0.6412 0.5104
-1.750 -0.0886 0.00735 0.00179 -0.0073 0.6343 0.6153
-1.500 -0.0652 0.00716 0.00177 -0.0063 0.6276 0.6775
-1.250 -0.0399 0.00708 0.00178 -0.0056 0.6214 0.7176
-1.000 -0.0143 0.00705 0.00181 -0.0049 0.6148 0.7528
-0.750 0.0116 0.00707 0.00185 -0.0042 0.6089 0.7779
-0.500 0.0384 0.00709 0.00188 -0.0038 0.6026 0.7947
-0.250 0.0653 0.00713 0.00189 -0.0034 0.5964 0.8070
0.000 0.0925 0.00716 0.00190 -0.0032 0.5905 0.8172
0.250 0.1200 0.00719 0.00192 -0.0029 0.5838 0.8242
0.500 0.1473 0.00724 0.00191 -0.0028 0.5763 0.8303
0.750 0.1748 0.00727 0.00191 -0.0026 0.5660 0.8348
1.000 0.2021 0.00731 0.00191 -0.0024 0.5541 0.8392
1.250 0.2292 0.00737 0.00191 -0.0022 0.5406 0.8440
1.500 0.2562 0.00743 0.00191 -0.0020 0.5267 0.8487
1.750 0.2833 0.00749 0.00194 -0.0018 0.5140 0.8527
2.000 0.3106 0.00755 0.00197 -0.0016 0.5030 0.8571
2.250 0.3377 0.00761 0.00201 -0.0015 0.4907 0.8619
2.500 0.3647 0.00769 0.00205 -0.0013 0.4773 0.8661
2.750 0.3915 0.00777 0.00211 -0.0010 0.4629 0.8703
3.000 0.4177 0.00789 0.00218 -0.0007 0.4431 0.8752
3.250 0.4435 0.00805 0.00224 -0.0003 0.4202 0.8802
3.500 0.4689 0.00823 0.00235 0.0001 0.3939 0.8845
3.750 0.4933 0.00848 0.00249 0.0007 0.3595 0.8896
4.000 0.5163 0.00885 0.00267 0.0014 0.3150 0.8952
4.250 0.5398 0.00920 0.00287 0.0021 0.2779 0.9002
4.500 0.5634 0.00953 0.00309 0.0028 0.2475 0.9060
4.750 0.5870 0.00985 0.00331 0.0034 0.2211 0.9121
5.250 0.6350 0.01047 0.00377 0.0046 0.1779 0.9244
5.500 0.6598 0.01074 0.00401 0.0050 0.1638 0.9307
5.750 0.6852 0.01102 0.00426 0.0053 0.1511 0.9373
6.000 0.7105 0.01131 0.00450 0.0056 0.1396 0.9445
6.250 0.7386 0.01158 0.00478 0.0052 0.1310 0.9505
6.500 0.7654 0.01189 0.00506 0.0052 0.1232 0.9578
6.750 0.7957 0.01217 0.00535 0.0043 0.1162 0.9629
7.000 0.8247 0.01251 0.00568 0.0037 0.1095 0.9691
7.250 0.8548 0.01279 0.00598 0.0028 0.1044 0.9744
7.500 0.8852 0.01316 0.00633 0.0018 0.0987 0.9793
7.750 0.9147 0.01348 0.00668 0.0010 0.0948 0.9849
8.000 0.9466 0.01381 0.00703 -0.0003 0.0902 0.9884
8.250 0.9763 0.01422 0.00744 -0.0013 0.0855 0.9931
8.500 1.0067 0.01458 0.00783 -0.0023 0.0822 0.9981
8.750 1.0294 0.01491 0.00819 -0.0018 0.0790 1.0000
9.000 1.0448 0.01524 0.00853 0.0003 0.0757 1.0000
9.250 1.0601 0.01564 0.00892 0.0023 0.0724 1.0000
9.500 1.0777 0.01595 0.00929 0.0039 0.0703 1.0000
9.750 1.0949 0.01631 0.00969 0.0055 0.0676 1.0000
10.000 1.1113 0.01674 0.01012 0.0072 0.0645 1.0000
10.250 1.1267 0.01721 0.01061 0.0090 0.0618 1.0000
10.500 1.1428 0.01760 0.01107 0.0107 0.0599 1.0000
10.750 1.1564 0.01803 0.01154 0.0128 0.0575 1.0000
11.000 1.1690 0.01854 0.01207 0.0150 0.0549 1.0000
11.250 1.1804 0.01915 0.01269 0.0172 0.0524 1.0000
11.500 1.1943 0.01967 0.01329 0.0189 0.0509 1.0000
11.750 1.2074 0.02027 0.01394 0.0206 0.0486 1.0000
12.000 1.2190 0.02098 0.01468 0.0223 0.0462 1.0000
12.250 1.2290 0.02184 0.01556 0.0240 0.0439 1.0000
12.500 1.2412 0.02261 0.01641 0.0254 0.0424 1.0000
12.750 1.2523 0.02349 0.01736 0.0267 0.0409 1.0000
13.000 1.2622 0.02450 0.01843 0.0280 0.0390 1.0000
13.250 1.2705 0.02569 0.01966 0.0292 0.0374 1.0000
13.500 1.2791 0.02691 0.02095 0.0302 0.0360 1.0000
13.750 1.2888 0.02811 0.02223 0.0310 0.0346 1.0000
14.000 1.2970 0.02946 0.02366 0.0318 0.0331 1.0000
14.250 1.3037 0.03101 0.02527 0.0324 0.0320 1.0000
14.500 1.3084 0.03279 0.02711 0.0330 0.0306 1.0000
14.750 1.3143 0.03452 0.02892 0.0334 0.0295 1.0000
15.000 1.3201 0.03631 0.03083 0.0337 0.0286 1.0000
15.250 1.3247 0.03826 0.03286 0.0339 0.0274 1.0000
15.500 1.3276 0.04043 0.03511 0.0339 0.0265 1.0000
15.750 1.3280 0.04292 0.03766 0.0338 0.0252 1.0000
16.000 1.3280 0.04552 0.04035 0.0336 0.0245 1.0000
16.250 1.3289 0.04809 0.04304 0.0333 0.0237 1.0000
16.500 1.3287 0.05088 0.04593 0.0327 0.0229 1.0000
16.750 1.3262 0.05401 0.04917 0.0320 0.0223 1.0000
17.000 1.3226 0.05742 0.05267 0.0310 0.0215 1.0000
17.250 1.3168 0.06125 0.05659 0.0298 0.0209 1.0000
17.500 1.3084 0.06557 0.06101 0.0282 0.0203 1.0000
17.750 1.3016 0.06983 0.06540 0.0265 0.0197 1.0000
18.000 1.2935 0.07443 0.07013 0.0245 0.0193 1.0000
18.250 1.2833 0.07949 0.07532 0.0222 0.0189 1.0000
18.500 1.2716 0.08494 0.08090 0.0197 0.0185 1.0000
18.750 1.2569 0.09111 0.08720 0.0166 0.0181 1.0000
19.000 1.2399 0.09783 0.09405 0.0131 0.0178 1.0000
19.250 1.2207 0.10513 0.10149 0.0093 0.0176 1.0000
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