EPPLER 585 AIRFOIL (e585-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 585 AIRFOIL (e585-il) Reynolds number: 500,000 Max Cl/Cd: 117.97 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e585-il-500000.txt Download as CSV file: xf-e585-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 585 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.0188 0.08491 0.08250 -0.1092 0.9172 0.0157
-10.750 -0.0111 0.08106 0.07859 -0.1116 0.9049 0.0162
-10.500 -0.0081 0.07688 0.07435 -0.1136 0.8935 0.0171
-10.250 -0.0149 0.07075 0.06816 -0.1169 0.8839 0.0184
-10.000 -0.0203 0.06525 0.06264 -0.1196 0.8744 0.0186
-9.750 -0.0226 0.06050 0.05784 -0.1217 0.8661 0.0186
-9.500 -0.0303 0.05435 0.05168 -0.1249 0.8583 0.0186
-9.250 -0.0409 0.04701 0.04427 -0.1302 0.8517 0.0186
-9.000 -0.0566 0.04207 0.03923 -0.1333 0.8436 0.0186
-8.750 -0.0777 0.03816 0.03517 -0.1347 0.8357 0.0186
-8.500 -0.0996 0.03532 0.03219 -0.1339 0.8276 0.0186
-8.000 -0.1382 0.04340 0.03975 -0.1371 0.8262 0.0186
-7.750 -0.1449 0.03885 0.03507 -0.1358 0.8202 0.0190
-7.500 -0.1339 0.03719 0.03341 -0.1351 0.8147 0.0195
-7.250 -0.1218 0.03573 0.03184 -0.1344 0.8098 0.0201
-7.000 -0.1111 0.03363 0.02955 -0.1334 0.8049 0.0209
-6.750 -0.1093 0.02993 0.02515 -0.1305 0.7996 0.0240
-6.500 -0.1023 0.02243 0.01692 -0.1273 0.7955 0.0152
-6.250 -0.0803 0.02039 0.01466 -0.1266 0.7918 0.0136
-6.000 -0.0586 0.01866 0.01266 -0.1257 0.7876 0.0135
-5.750 -0.0343 0.01761 0.01138 -0.1251 0.7838 0.0140
-5.500 -0.0095 0.01631 0.00987 -0.1246 0.7804 0.0139
-5.250 0.0157 0.01512 0.00850 -0.1241 0.7771 0.0136
-5.000 0.0397 0.01418 0.00749 -0.1234 0.7733 0.0134
-4.750 0.0642 0.01345 0.00668 -0.1229 0.7696 0.0135
-4.500 0.0892 0.01284 0.00601 -0.1225 0.7662 0.0138
-4.250 0.1151 0.01236 0.00543 -0.1223 0.7631 0.0143
-4.000 0.1396 0.01178 0.00482 -0.1219 0.7596 0.0155
-3.750 0.1655 0.01142 0.00444 -0.1217 0.7559 0.0182
-3.500 0.1914 0.01087 0.00394 -0.1216 0.7526 0.0342
-3.250 0.2175 0.01035 0.00367 -0.1217 0.7494 0.0979
-3.000 0.2437 0.00983 0.00350 -0.1220 0.7462 0.1975
-2.750 0.2676 0.00883 0.00328 -0.1224 0.7427 0.4172
-2.500 0.2915 0.00807 0.00340 -0.1221 0.7391 0.6785
-2.250 0.3194 0.00818 0.00348 -0.1220 0.7358 0.7161
-2.000 0.3483 0.00833 0.00353 -0.1221 0.7327 0.7353
-1.750 0.3755 0.00847 0.00365 -0.1219 0.7292 0.7504
-1.500 0.4021 0.00859 0.00377 -0.1215 0.7253 0.7617
-1.250 0.4297 0.00870 0.00382 -0.1213 0.7216 0.7714
-1.000 0.4576 0.00882 0.00388 -0.1213 0.7184 0.7796
-0.750 0.4849 0.00895 0.00397 -0.1211 0.7150 0.7871
-0.500 0.5108 0.00910 0.00413 -0.1205 0.7112 0.7979
-0.250 0.5351 0.00924 0.00429 -0.1194 0.7074 0.8072
0.000 0.5628 0.00934 0.00434 -0.1194 0.7040 0.8152
0.250 0.5900 0.00940 0.00436 -0.1193 0.7006 0.8184
0.500 0.6165 0.00940 0.00438 -0.1191 0.6965 0.8213
0.750 0.6445 0.00941 0.00435 -0.1193 0.6922 0.8241
1.000 0.6736 0.00942 0.00430 -0.1198 0.6883 0.8267
1.250 0.7025 0.00946 0.00431 -0.1203 0.6841 0.8292
1.500 0.7291 0.00942 0.00429 -0.1202 0.6794 0.8311
1.750 0.7566 0.00942 0.00427 -0.1203 0.6750 0.8329
2.000 0.7853 0.00947 0.00428 -0.1206 0.6710 0.8350
2.250 0.8112 0.00946 0.00431 -0.1204 0.6659 0.8372
2.500 0.8387 0.00946 0.00431 -0.1206 0.6607 0.8394
2.750 0.8677 0.00951 0.00430 -0.1210 0.6560 0.8416
3.000 0.8942 0.00952 0.00436 -0.1210 0.6502 0.8442
3.250 0.9207 0.00951 0.00435 -0.1209 0.6446 0.8462
3.500 0.9473 0.00955 0.00438 -0.1209 0.6392 0.8480
3.750 0.9727 0.00956 0.00444 -0.1206 0.6327 0.8501
4.000 0.9997 0.00961 0.00447 -0.1206 0.6269 0.8523
4.250 1.0249 0.00964 0.00456 -0.1203 0.6197 0.8550
4.500 1.0513 0.00970 0.00460 -0.1203 0.6128 0.8577
4.750 1.0767 0.00975 0.00470 -0.1201 0.6048 0.8601
5.000 1.1012 0.00981 0.00475 -0.1196 0.5970 0.8622
5.250 1.1247 0.00986 0.00486 -0.1189 0.5876 0.8646
5.500 1.1484 0.00995 0.00497 -0.1183 0.5784 0.8673
5.750 1.1716 0.01007 0.00509 -0.1176 0.5680 0.8703
6.000 1.1948 0.01019 0.00524 -0.1170 0.5568 0.8735
6.250 1.2163 0.01032 0.00539 -0.1160 0.5450 0.8764
6.500 1.2363 0.01048 0.00556 -0.1147 0.5321 0.8795
6.750 1.2554 0.01067 0.00575 -0.1132 0.5178 0.8830
7.000 1.2735 0.01090 0.00598 -0.1116 0.5018 0.8868
7.250 1.2884 0.01116 0.00622 -0.1094 0.4844 0.8908
7.500 1.2992 0.01145 0.00649 -0.1063 0.4666 0.8956
8.000 1.3201 0.01227 0.00724 -0.1004 0.4285 0.9073
8.250 1.3282 0.01276 0.00771 -0.0971 0.4078 0.9144
8.500 1.3340 0.01333 0.00824 -0.0935 0.3874 0.9231
8.750 1.3400 0.01388 0.00878 -0.0901 0.3669 0.9354
9.000 1.3458 0.01454 0.00942 -0.0868 0.3453 0.9682
9.250 1.3561 0.01542 0.01022 -0.0850 0.3227 1.0000
9.500 1.3649 0.01643 0.01114 -0.0829 0.3005 1.0000
9.750 1.3728 0.01750 0.01214 -0.0808 0.2789 1.0000
10.000 1.3799 0.01865 0.01321 -0.0787 0.2578 1.0000
10.250 1.3859 0.01991 0.01439 -0.0765 0.2383 1.0000
10.500 1.3931 0.02115 0.01557 -0.0746 0.2192 1.0000
10.750 1.3992 0.02249 0.01684 -0.0727 0.2008 1.0000
11.000 1.4045 0.02394 0.01822 -0.0707 0.1834 1.0000
11.250 1.4096 0.02544 0.01967 -0.0689 0.1663 1.0000
11.500 1.4152 0.02696 0.02114 -0.0672 0.1501 1.0000
11.750 1.4198 0.02860 0.02272 -0.0656 0.1337 1.0000
12.000 1.4241 0.03030 0.02437 -0.0640 0.1189 1.0000
12.250 1.4282 0.03208 0.02610 -0.0625 0.1051 1.0000
12.500 1.4312 0.03399 0.02795 -0.0610 0.0912 1.0000
12.750 1.4332 0.03606 0.02995 -0.0596 0.0774 1.0000
13.000 1.4362 0.03810 0.03197 -0.0584 0.0661 1.0000
13.250 1.4375 0.04036 0.03417 -0.0572 0.0542 1.0000
13.500 1.4407 0.04252 0.03632 -0.0562 0.0462 1.0000
13.750 1.4423 0.04489 0.03867 -0.0553 0.0379 1.0000
14.000 1.4462 0.04711 0.04092 -0.0545 0.0327 1.0000
14.250 1.4482 0.04958 0.04340 -0.0538 0.0273 1.0000
14.500 1.4493 0.05222 0.04606 -0.0532 0.0234 1.0000
14.750 1.4527 0.05468 0.04858 -0.0528 0.0203 1.0000
15.000 1.4540 0.05742 0.05137 -0.0525 0.0176 1.0000
15.250 1.4557 0.06022 0.05425 -0.0522 0.0154 1.0000
15.500 1.4560 0.06325 0.05734 -0.0521 0.0133 1.0000
15.750 1.4564 0.06632 0.06048 -0.0521 0.0116 1.0000
16.000 1.4551 0.06970 0.06394 -0.0522 0.0100 1.0000
16.250 1.4542 0.07312 0.06745 -0.0525 0.0089 1.0000
16.500 1.4509 0.07695 0.07137 -0.0529 0.0076 1.0000
16.750 1.4482 0.08077 0.07528 -0.0535 0.0065 1.0000
17.000 1.4415 0.08529 0.07991 -0.0543 0.0056 1.0000
17.250 1.4384 0.08936 0.08409 -0.0552 0.0049 1.0000
17.500 1.4286 0.09458 0.08941 -0.0566 0.0044 1.0000
17.750 1.4216 0.09948 0.09445 -0.0580 0.0037 1.0000
18.000 1.4157 0.10428 0.09938 -0.0596 0.0036 1.0000
18.250 1.4074 0.10955 0.10476 -0.0614 0.0032 1.0000
18.500 1.3955 0.11558 0.11093 -0.0638 0.0030 1.0000
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