EPPLER STE 87(-3)-914 AIRFOIL (ste87391-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER STE 87(-3)-914 AIRFOIL (ste87391-il) Reynolds number: 500,000 Max Cl/Cd: 97.38 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ste87391-il-500000.txt Download as CSV file: xf-ste87391-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER STE 87(-3)-914 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
------ -------- --------- --------- -------- -------- --------
-14.000 -0.1626 0.12495 0.12223 -0.1216 0.9706 0.0239
-13.750 -0.1757 0.11631 0.11363 -0.1258 0.9698 0.0258
-13.500 -0.2995 0.07899 0.07617 -0.1436 0.9686 0.0193
-13.250 -0.2907 0.07668 0.07389 -0.1449 0.9680 0.0195
-13.000 -0.2912 0.07231 0.06951 -0.1484 0.9675 0.0198
-12.750 -0.4306 0.05275 0.04922 -0.1583 0.9591 0.0159
-12.500 -0.4728 0.05415 0.05073 -0.1455 0.9525 0.0158
-12.250 -0.4899 0.05063 0.04708 -0.1461 0.9505 0.0157
-12.000 -0.5037 0.04724 0.04352 -0.1473 0.9491 0.0157
-11.750 -0.5493 0.04853 0.04490 -0.1344 0.9431 0.0157
-11.500 -0.5687 0.04626 0.04249 -0.1321 0.9401 0.0156
-11.250 -0.5823 0.04379 0.03981 -0.1311 0.9382 0.0156
-11.000 -0.6219 0.04412 0.04018 -0.1201 0.9319 0.0156
-10.750 -0.6277 0.04155 0.03733 -0.1185 0.9292 0.0156
-10.500 -0.6187 0.03890 0.03413 -0.1198 0.9272 0.0160
-10.250 -0.5986 0.03606 0.03128 -0.1209 0.9267 0.0166
-10.000 -0.6181 0.03572 0.03093 -0.1130 0.9205 0.0167
-9.750 -0.5989 0.03464 0.02980 -0.1129 0.9185 0.0173
-9.500 -0.5787 0.03283 0.02773 -0.1133 0.9171 0.0178
-9.250 -0.5545 0.03099 0.02561 -0.1140 0.9161 0.0181
-9.000 -0.5269 0.02950 0.02387 -0.1151 0.9154 0.0184
-8.750 -0.4961 0.02836 0.02248 -0.1165 0.9147 0.0188
-8.500 -0.4884 0.02788 0.02183 -0.1133 0.9099 0.0190
-8.250 -0.4689 0.02641 0.02034 -0.1126 0.9079 0.0194
-8.000 -0.4429 0.02548 0.01941 -0.1130 0.9062 0.0199
-7.750 -0.4132 0.02474 0.01863 -0.1139 0.9049 0.0206
-7.500 -0.3815 0.02411 0.01792 -0.1152 0.9038 0.0216
-7.250 -0.3492 0.02356 0.01726 -0.1165 0.9030 0.0223
-7.000 -0.3165 0.02256 0.01629 -0.1182 0.9024 0.0230
-6.750 -0.2819 0.02196 0.01567 -0.1201 0.9019 0.0238
-6.500 -0.2463 0.02145 0.01511 -0.1221 0.9014 0.0248
-6.250 -0.2394 0.02130 0.01493 -0.1186 0.8948 0.0253
-6.000 -0.2080 0.02075 0.01435 -0.1199 0.8930 0.0263
-5.750 -0.1748 0.02035 0.01393 -0.1214 0.8916 0.0281
-5.500 -0.1403 0.01994 0.01350 -0.1231 0.8906 0.0303
-5.250 -0.1050 0.01961 0.01313 -0.1248 0.8897 0.0330
-5.000 -0.0686 0.01921 0.01276 -0.1268 0.8890 0.0402
-4.750 -0.0281 0.01817 0.01236 -0.1305 0.8887 0.1650
-4.500 0.0077 0.01799 0.01227 -0.1324 0.8881 0.1953
-4.250 0.0439 0.01785 0.01216 -0.1342 0.8876 0.2143
-4.000 0.0525 0.01803 0.01234 -0.1309 0.8798 0.2226
-3.750 0.0850 0.01790 0.01223 -0.1320 0.8780 0.2369
-3.500 0.1197 0.01770 0.01209 -0.1336 0.8767 0.2540
-3.250 0.1556 0.01747 0.01189 -0.1353 0.8757 0.2695
-3.000 0.1924 0.01721 0.01169 -0.1373 0.8749 0.2874
-2.750 0.2304 0.01690 0.01146 -0.1395 0.8742 0.3117
-2.500 0.2694 0.01655 0.01120 -0.1419 0.8737 0.3429
-2.250 0.2863 0.01658 0.01136 -0.1402 0.8667 0.3755
-2.000 0.3221 0.01618 0.01116 -0.1421 0.8644 0.4344
-1.750 0.3626 0.01563 0.01089 -0.1449 0.8633 0.5187
-1.500 0.4039 0.01500 0.01070 -0.1478 0.8624 0.6368
-1.250 0.4400 0.01464 0.01050 -0.1490 0.8613 0.7063
-1.000 0.4772 0.01423 0.01009 -0.1504 0.8602 0.7303
-0.750 0.5170 0.01369 0.00952 -0.1524 0.8595 0.7469
-0.500 0.5546 0.01310 0.00895 -0.1537 0.8588 0.7577
-0.250 0.5675 0.01341 0.00924 -0.1508 0.8496 0.7675
0.000 0.5995 0.01302 0.00889 -0.1512 0.8478 0.7744
0.250 0.6339 0.01259 0.00845 -0.1521 0.8466 0.7818
0.500 0.6698 0.01213 0.00798 -0.1534 0.8456 0.7882
0.750 0.7038 0.01166 0.00754 -0.1543 0.8445 0.7936
1.000 0.7400 0.01120 0.00708 -0.1556 0.8433 0.7995
1.250 0.7482 0.01157 0.00747 -0.1518 0.8320 0.8050
1.500 0.7817 0.01109 0.00700 -0.1526 0.8295 0.8089
1.750 0.7917 0.01134 0.00730 -0.1490 0.8178 0.8134
2.000 0.8248 0.01092 0.00688 -0.1498 0.8135 0.8182
2.250 0.8426 0.01108 0.00705 -0.1479 0.8001 0.8232
2.500 0.8660 0.01089 0.00689 -0.1467 0.7874 0.8288
2.750 0.8962 0.01054 0.00653 -0.1466 0.7736 0.8385
3.000 0.9286 0.01014 0.00607 -0.1469 0.7553 0.8469
3.250 0.9600 0.00994 0.00576 -0.1473 0.7286 0.8525
3.500 0.9845 0.01011 0.00573 -0.1466 0.6938 0.8563
3.750 1.0015 0.01052 0.00593 -0.1446 0.6567 0.8592
4.000 1.0129 0.01096 0.00621 -0.1415 0.6211 0.8617
4.250 1.0240 0.01148 0.00657 -0.1384 0.5863 0.8642
4.500 1.0353 0.01205 0.00699 -0.1355 0.5521 0.8664
5.000 1.0605 0.01326 0.00788 -0.1304 0.4856 0.8708
5.250 1.0748 0.01387 0.00833 -0.1284 0.4555 0.8725
5.500 1.0912 0.01442 0.00878 -0.1267 0.4277 0.8744
5.750 1.1074 0.01498 0.00922 -0.1250 0.4018 0.8760
6.000 1.1233 0.01552 0.00965 -0.1232 0.3781 0.8774
6.250 1.1398 0.01605 0.01009 -0.1216 0.3566 0.8788
6.500 1.1571 0.01656 0.01053 -0.1201 0.3377 0.8803
6.750 1.1755 0.01704 0.01097 -0.1189 0.3214 0.8818
7.000 1.1942 0.01752 0.01141 -0.1177 0.3070 0.8834
7.250 1.2124 0.01803 0.01188 -0.1164 0.2945 0.8854
7.500 1.2310 0.01853 0.01236 -0.1153 0.2833 0.8874
7.750 1.2503 0.01901 0.01283 -0.1142 0.2722 0.8889
8.000 1.2678 0.01959 0.01336 -0.1130 0.2602 0.8905
8.250 1.2863 0.02011 0.01385 -0.1119 0.2480 0.8920
8.500 1.3047 0.02058 0.01431 -0.1108 0.2358 0.8937
8.750 1.3218 0.02112 0.01483 -0.1094 0.2249 0.8955
9.000 1.3394 0.02165 0.01537 -0.1082 0.2157 0.8975
9.250 1.3573 0.02217 0.01590 -0.1071 0.2065 0.8996
9.500 1.3735 0.02281 0.01651 -0.1057 0.1963 0.9019
9.750 1.3905 0.02342 0.01711 -0.1045 0.1839 0.9042
10.000 1.4074 0.02406 0.01773 -0.1033 0.1716 0.9065
10.250 1.4215 0.02478 0.01842 -0.1017 0.1574 0.9095
10.500 1.4342 0.02558 0.01917 -0.0999 0.1387 0.9129
10.750 1.4413 0.02682 0.02022 -0.0974 0.1072 0.9164
11.000 1.4392 0.02873 0.02185 -0.0938 0.0681 0.9201
11.250 1.4333 0.03096 0.02382 -0.0898 0.0332 0.9241
11.500 1.4307 0.03295 0.02572 -0.0863 0.0170 0.9296
11.750 1.4355 0.03444 0.02725 -0.0838 0.0135 0.9371
12.250 1.4455 0.03720 0.03019 -0.0791 0.0112 0.9981
12.500 1.4539 0.03878 0.03187 -0.0776 0.0105 0.9981
12.750 1.4606 0.04052 0.03370 -0.0761 0.0099 0.9981
13.000 1.4634 0.04262 0.03588 -0.0743 0.0094 0.9981
13.250 1.4629 0.04508 0.03844 -0.0724 0.0091 0.9981
13.500 1.4665 0.04724 0.04070 -0.0710 0.0089 0.9981
13.750 1.4679 0.04966 0.04324 -0.0695 0.0086 0.9981
14.000 1.4677 0.05231 0.04600 -0.0682 0.0084 0.9981
14.250 1.4663 0.05517 0.04896 -0.0670 0.0082 0.9981
14.500 1.4633 0.05832 0.05222 -0.0659 0.0081 0.9981
14.750 1.4593 0.06167 0.05568 -0.0651 0.0080 0.9981
15.000 1.4538 0.06531 0.05943 -0.0645 0.0079 0.9981
15.250 1.4473 0.06919 0.06342 -0.0641 0.0078 0.9981
15.500 1.4398 0.07332 0.06767 -0.0640 0.0077 0.9981
15.750 1.4310 0.07775 0.07220 -0.0641 0.0076 0.9981
16.000 1.4214 0.08238 0.07694 -0.0645 0.0075 0.9981
16.250 1.4118 0.08710 0.08178 -0.0651 0.0075 0.9981
16.500 1.4015 0.09200 0.08678 -0.0659 0.0074 0.9981
16.750 1.3914 0.09693 0.09181 -0.0668 0.0074 0.9981
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