S3014-095-85 (s3014-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: S3014-095-85 (s3014-il) Reynolds number: 500,000 Max Cl/Cd: 92.36 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s3014-il-500000.txt Download as CSV file: xf-s3014-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: S3014-095-85
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4465 0.10192 0.09969 -0.0177 1.0000 0.0180
-9.750 -0.4433 0.09789 0.09568 -0.0197 1.0000 0.0180
-9.500 -0.4522 0.09193 0.08976 -0.0213 1.0000 0.0188
-9.250 -0.4470 0.08915 0.08699 -0.0221 1.0000 0.0192
-9.000 -0.4444 0.08566 0.08353 -0.0238 1.0000 0.0195
-8.750 -0.4421 0.08221 0.08010 -0.0256 1.0000 0.0198
-8.500 -0.4415 0.07853 0.07646 -0.0276 1.0000 0.0202
-8.250 -0.4435 0.07452 0.07249 -0.0303 1.0000 0.0204
-8.000 -0.4500 0.07029 0.06832 -0.0336 1.0000 0.0209
-7.750 -0.4535 0.06467 0.06272 -0.0395 1.0000 0.0214
-7.500 -0.4496 0.05788 0.05586 -0.0466 0.9924 0.0218
-7.000 -0.4236 0.03760 0.03451 -0.0620 0.9603 0.0258
-6.750 -0.4079 0.03531 0.03219 -0.0619 0.9494 0.0267
-6.500 -0.3918 0.03377 0.03055 -0.0610 0.9394 0.0277
-6.250 -0.3763 0.03194 0.02852 -0.0599 0.9298 0.0294
-6.000 -0.3500 0.03310 0.02931 -0.0583 0.9210 0.0337
-5.750 -0.3451 0.02669 0.02253 -0.0573 0.9125 0.0362
-5.500 -0.3235 0.02558 0.02139 -0.0567 0.9049 0.0384
-5.250 -0.3057 0.01805 0.01270 -0.0530 0.8982 0.0227
-5.000 -0.2820 0.01618 0.01054 -0.0520 0.8913 0.0221
-4.750 -0.2578 0.01490 0.00905 -0.0509 0.8856 0.0220
-4.500 -0.2322 0.01392 0.00795 -0.0503 0.8787 0.0224
-4.250 -0.2070 0.01321 0.00711 -0.0495 0.8729 0.0232
-4.000 -0.1815 0.01241 0.00621 -0.0489 0.8663 0.0235
-3.750 -0.1562 0.01172 0.00542 -0.0481 0.8600 0.0239
-3.500 -0.1305 0.01117 0.00480 -0.0475 0.8538 0.0244
-3.250 -0.1045 0.01074 0.00429 -0.0470 0.8470 0.0249
-3.000 -0.0791 0.01015 0.00359 -0.0463 0.8409 0.0262
-2.750 -0.0525 0.00978 0.00317 -0.0458 0.8337 0.0284
-2.500 -0.0258 0.00953 0.00287 -0.0454 0.8276 0.0319
-2.250 0.0012 0.00922 0.00257 -0.0450 0.8200 0.0430
-2.000 0.0257 0.00853 0.00230 -0.0445 0.8136 0.1595
-1.750 0.0513 0.00803 0.00217 -0.0442 0.8055 0.2633
-1.500 0.0766 0.00763 0.00205 -0.0437 0.7982 0.3622
-1.250 0.1010 0.00712 0.00196 -0.0431 0.7893 0.4934
-1.000 0.1237 0.00659 0.00192 -0.0420 0.7807 0.6401
-0.750 0.1445 0.00610 0.00189 -0.0402 0.7719 0.7834
-0.500 0.1936 0.00576 0.00193 -0.0438 0.7622 0.9531
-0.250 0.2404 0.00580 0.00188 -0.0476 0.7521 0.9818
0.000 0.2862 0.00582 0.00179 -0.0513 0.7418 0.9947
0.250 0.3248 0.00582 0.00170 -0.0536 0.7299 1.0000
0.500 0.3499 0.00584 0.00165 -0.0530 0.7178 1.0000
0.750 0.3751 0.00587 0.00161 -0.0524 0.7054 1.0000
1.000 0.4004 0.00591 0.00158 -0.0518 0.6921 1.0000
1.250 0.4258 0.00597 0.00157 -0.0512 0.6781 1.0000
1.500 0.4513 0.00604 0.00156 -0.0507 0.6633 1.0000
1.750 0.4768 0.00613 0.00157 -0.0501 0.6473 1.0000
2.000 0.5022 0.00623 0.00160 -0.0495 0.6306 1.0000
2.250 0.5276 0.00635 0.00163 -0.0490 0.6132 1.0000
2.500 0.5531 0.00647 0.00168 -0.0484 0.5942 1.0000
2.750 0.5784 0.00662 0.00175 -0.0479 0.5739 1.0000
3.000 0.6037 0.00677 0.00183 -0.0474 0.5531 1.0000
3.250 0.6289 0.00695 0.00192 -0.0468 0.5307 1.0000
3.500 0.6539 0.00715 0.00203 -0.0463 0.5068 1.0000
3.750 0.6787 0.00737 0.00217 -0.0457 0.4822 1.0000
4.000 0.7033 0.00762 0.00231 -0.0451 0.4558 1.0000
4.250 0.7278 0.00788 0.00247 -0.0445 0.4284 1.0000
4.500 0.7520 0.00817 0.00265 -0.0439 0.3999 1.0000
4.750 0.7762 0.00848 0.00287 -0.0433 0.3719 1.0000
5.000 0.8002 0.00881 0.00308 -0.0426 0.3444 1.0000
5.250 0.8242 0.00914 0.00332 -0.0420 0.3189 1.0000
5.500 0.8482 0.00948 0.00357 -0.0414 0.2967 1.0000
5.750 0.8722 0.00982 0.00385 -0.0409 0.2750 1.0000
6.000 0.8960 0.01018 0.00413 -0.0402 0.2563 1.0000
6.250 0.9200 0.01050 0.00442 -0.0397 0.2385 1.0000
6.500 0.9439 0.01085 0.00472 -0.0391 0.2209 1.0000
6.750 0.9674 0.01123 0.00505 -0.0385 0.2033 1.0000
7.000 0.9906 0.01163 0.00538 -0.0378 0.1851 1.0000
7.250 1.0137 0.01202 0.00572 -0.0372 0.1657 1.0000
7.500 1.0363 0.01247 0.00609 -0.0365 0.1477 1.0000
7.750 1.0587 0.01293 0.00649 -0.0358 0.1314 1.0000
8.000 1.0811 0.01338 0.00691 -0.0351 0.1160 1.0000
8.250 1.1029 0.01387 0.00735 -0.0343 0.1005 1.0000
8.500 1.1243 0.01439 0.00782 -0.0335 0.0865 1.0000
8.750 1.1449 0.01496 0.00834 -0.0326 0.0718 1.0000
9.000 1.1640 0.01566 0.00894 -0.0315 0.0546 1.0000
9.250 1.1775 0.01687 0.00993 -0.0297 0.0249 1.0000
9.500 1.1906 0.01808 0.01106 -0.0277 0.0134 1.0000
9.750 1.2075 0.01887 0.01192 -0.0262 0.0114 1.0000
10.000 1.2215 0.01985 0.01298 -0.0244 0.0101 1.0000
10.250 1.2347 0.02081 0.01405 -0.0225 0.0095 1.0000
10.500 1.2460 0.02170 0.01505 -0.0202 0.0091 1.0000
10.750 1.2545 0.02262 0.01607 -0.0176 0.0088 1.0000
11.000 1.2606 0.02374 0.01730 -0.0150 0.0086 1.0000
11.250 1.2668 0.02491 0.01857 -0.0126 0.0083 1.0000
11.500 1.2714 0.02628 0.02005 -0.0104 0.0079 1.0000
11.750 1.2752 0.02778 0.02166 -0.0084 0.0078 1.0000
12.000 1.2774 0.02949 0.02349 -0.0065 0.0077 1.0000
12.250 1.2761 0.03161 0.02571 -0.0048 0.0074 1.0000
12.500 1.2755 0.03380 0.02801 -0.0034 0.0073 1.0000
12.750 1.2675 0.03685 0.03119 -0.0020 0.0070 1.0000
13.000 1.2708 0.03893 0.03339 -0.0014 0.0071 1.0000
13.250 1.2627 0.04235 0.03694 -0.0007 0.0070 1.0000
13.500 1.2605 0.04530 0.04001 -0.0005 0.0070 1.0000
13.750 1.2522 0.04909 0.04395 -0.0004 0.0069 1.0000
14.000 1.2428 0.05324 0.04826 -0.0006 0.0068 1.0000
14.250 1.2330 0.05761 0.05280 -0.0010 0.0068 1.0000
14.500 1.2313 0.06105 0.05636 -0.0020 0.0068 1.0000
14.750 1.2251 0.06529 0.06074 -0.0032 0.0068 1.0000
15.000 1.2116 0.07081 0.06644 -0.0048 0.0068 1.0000
15.250 1.2132 0.07424 0.06997 -0.0066 0.0068 1.0000
15.500 1.2009 0.08000 0.07589 -0.0089 0.0068 1.0000
15.750 1.1903 0.08576 0.08181 -0.0115 0.0068 1.0000
16.000 1.1837 0.09105 0.08723 -0.0143 0.0069 1.0000
16.250 1.1739 0.09709 0.09340 -0.0175 0.0069 1.0000
16.500 1.1621 0.10373 0.10019 -0.0211 0.0069 1.0000
16.750 1.1544 0.10980 0.10638 -0.0246 0.0070 1.0000
17.000 1.1414 0.11711 0.11384 -0.0288 0.0070 1.0000
17.250 1.1309 0.12415 0.12103 -0.0330 0.0070 1.0000
17.500 1.1201 0.13149 0.12850 -0.0374 0.0071 1.0000
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Polar data table (+)
Polar graphs
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