GOE 514 AIRFOIL (goe514-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 514 AIRFOIL (goe514-il) Reynolds number: 1,000,000 Max Cl/Cd: 78.05 at α=9° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe514-il-1000000-n5.txt Download as CSV file: xf-goe514-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 514 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.250 -0.4087 0.08597 0.08322 -0.1200 0.9730 0.0085
-16.000 -0.4182 0.08125 0.07845 -0.1225 0.9697 0.0086
-15.750 -0.4303 0.07595 0.07309 -0.1257 0.9667 0.0085
-15.500 -0.4432 0.07010 0.06718 -0.1301 0.9642 0.0086
-15.250 -0.4565 0.06385 0.06084 -0.1356 0.9619 0.0085
-15.000 -0.4809 0.05620 0.05308 -0.1426 0.9581 0.0086
-14.750 -0.6368 0.03199 0.02827 -0.1649 0.9380 0.0082
-14.500 -0.6343 0.02762 0.02366 -0.1674 0.9325 0.0082
-14.250 -0.6213 0.02479 0.02066 -0.1684 0.9285 0.0084
-14.000 -0.6064 0.02294 0.01869 -0.1682 0.9246 0.0085
-13.750 -0.5919 0.02171 0.01734 -0.1672 0.9205 0.0086
-13.500 -0.5751 0.02068 0.01620 -0.1663 0.9168 0.0088
-13.250 -0.5576 0.01980 0.01522 -0.1654 0.9133 0.0089
-13.000 -0.5499 0.01912 0.01446 -0.1622 0.9092 0.0090
-12.750 -0.5353 0.01854 0.01381 -0.1601 0.9050 0.0092
-12.500 -0.5173 0.01794 0.01312 -0.1587 0.9013 0.0093
-12.250 -0.4976 0.01732 0.01241 -0.1576 0.8983 0.0095
-12.000 -0.4832 0.01667 0.01168 -0.1555 0.8954 0.0097
-11.750 -0.4694 0.01619 0.01115 -0.1530 0.8921 0.0099
-11.500 -0.4536 0.01570 0.01061 -0.1509 0.8883 0.0102
-11.250 -0.4339 0.01526 0.01012 -0.1494 0.8848 0.0105
-11.000 -0.4114 0.01482 0.00959 -0.1486 0.8808 0.0108
-10.750 -0.3945 0.01447 0.00920 -0.1464 0.8767 0.0112
-10.500 -0.3764 0.01415 0.00883 -0.1445 0.8719 0.0115
-10.250 -0.3552 0.01381 0.00842 -0.1432 0.8664 0.0118
-10.000 -0.3343 0.01345 0.00800 -0.1418 0.8616 0.0120
-9.750 -0.3164 0.01308 0.00759 -0.1398 0.8564 0.0126
-9.500 -0.2958 0.01274 0.00719 -0.1384 0.8509 0.0130
-9.250 -0.2741 0.01244 0.00684 -0.1371 0.8453 0.0135
-9.000 -0.2549 0.01217 0.00653 -0.1352 0.8364 0.0141
-8.750 -0.2339 0.01193 0.00621 -0.1337 0.8275 0.0146
-8.500 -0.2142 0.01168 0.00590 -0.1319 0.8159 0.0154
-8.250 -0.1953 0.01144 0.00559 -0.1300 0.8013 0.0164
-8.000 -0.1792 0.01129 0.00533 -0.1274 0.7793 0.0173
-7.750 -0.1661 0.01119 0.00510 -0.1241 0.7537 0.0188
-7.250 -0.1361 0.01093 0.00466 -0.1185 0.7188 0.0240
-7.000 -0.1200 0.01079 0.00446 -0.1159 0.7036 0.0280
-6.750 -0.1036 0.01064 0.00427 -0.1134 0.6898 0.0338
-6.500 -0.0866 0.01049 0.00409 -0.1110 0.6788 0.0405
-6.250 -0.0694 0.01034 0.00394 -0.1087 0.6689 0.0475
-6.000 -0.0529 0.01022 0.00381 -0.1061 0.6605 0.0528
-5.750 -0.0358 0.01013 0.00369 -0.1037 0.6506 0.0570
-5.500 -0.0180 0.01005 0.00358 -0.1015 0.6423 0.0607
-5.250 -0.0011 0.01001 0.00348 -0.0990 0.6308 0.0634
-5.000 0.0170 0.00994 0.00337 -0.0968 0.6198 0.0662
-4.750 0.0341 0.00988 0.00327 -0.0944 0.6099 0.0695
-4.500 0.0525 0.00984 0.00319 -0.0923 0.5988 0.0726
-4.250 0.0700 0.00983 0.00312 -0.0900 0.5871 0.0751
-4.000 0.0863 0.00980 0.00304 -0.0874 0.5724 0.0795
-3.750 0.1026 0.00980 0.00298 -0.0849 0.5560 0.0841
-3.500 0.1169 0.00985 0.00295 -0.0820 0.5337 0.0906
-3.250 0.1294 0.00985 0.00296 -0.0788 0.5092 0.1139
-3.000 0.1441 0.00995 0.00301 -0.0760 0.4849 0.1293
-2.750 0.1603 0.01009 0.00305 -0.0736 0.4638 0.1340
-2.500 0.1774 0.01021 0.00309 -0.0713 0.4477 0.1383
-2.250 0.1952 0.01030 0.00313 -0.0692 0.4346 0.1422
-2.000 0.2141 0.01039 0.00316 -0.0673 0.4238 0.1449
-1.750 0.2342 0.01046 0.00319 -0.0656 0.4151 0.1480
-1.500 0.2545 0.01054 0.00321 -0.0640 0.4080 0.1496
-1.250 0.2747 0.01062 0.00324 -0.0624 0.4017 0.1509
-1.000 0.2955 0.01068 0.00327 -0.0609 0.3964 0.1522
-0.750 0.3156 0.01073 0.00329 -0.0593 0.3910 0.1549
-0.500 0.3355 0.01080 0.00334 -0.0576 0.3858 0.1583
-0.250 0.3568 0.01083 0.00337 -0.0563 0.3817 0.1606
0.000 0.3776 0.01089 0.00342 -0.0548 0.3770 0.1634
0.250 0.3971 0.01099 0.00348 -0.0532 0.3712 0.1651
0.500 0.4175 0.01107 0.00354 -0.0517 0.3676 0.1668
0.750 0.4389 0.01114 0.00359 -0.0504 0.3643 0.1682
1.250 0.4804 0.01129 0.00372 -0.0476 0.3568 0.1744
1.500 0.5000 0.01138 0.00381 -0.0460 0.3529 0.1789
1.750 0.5202 0.01147 0.00390 -0.0445 0.3500 0.1850
2.000 0.5406 0.01153 0.00400 -0.0431 0.3468 0.1946
2.250 0.5608 0.01160 0.00410 -0.0417 0.3438 0.2071
2.500 0.5802 0.01169 0.00424 -0.0402 0.3395 0.2292
2.750 0.6002 0.01182 0.00436 -0.0388 0.3362 0.2373
3.000 0.6203 0.01194 0.00450 -0.0374 0.3333 0.2467
3.250 0.6412 0.01205 0.00463 -0.0362 0.3311 0.2529
3.500 0.6620 0.01217 0.00477 -0.0349 0.3285 0.2601
3.750 0.6827 0.01231 0.00490 -0.0337 0.3257 0.2651
4.000 0.7030 0.01246 0.00506 -0.0324 0.3228 0.2703
4.250 0.7227 0.01263 0.00523 -0.0311 0.3198 0.2747
4.500 0.7423 0.01281 0.00541 -0.0297 0.3168 0.2802
4.750 0.7633 0.01296 0.00557 -0.0287 0.3150 0.2844
5.000 0.7839 0.01311 0.00575 -0.0275 0.3122 0.2891
5.250 0.8045 0.01327 0.00593 -0.0264 0.3096 0.2940
5.500 0.8243 0.01348 0.00612 -0.0252 0.3064 0.2984
5.750 0.8426 0.01372 0.00636 -0.0238 0.3026 0.3021
6.000 0.8624 0.01392 0.00658 -0.0226 0.2998 0.3071
6.250 0.8832 0.01410 0.00679 -0.0216 0.2982 0.3112
6.500 0.9033 0.01431 0.00701 -0.0206 0.2942 0.3157
6.750 0.9229 0.01454 0.00725 -0.0194 0.2909 0.3203
7.000 0.9421 0.01479 0.00752 -0.0183 0.2888 0.3263
7.250 0.9603 0.01508 0.00782 -0.0170 0.2856 0.3331
7.500 0.9806 0.01530 0.00808 -0.0161 0.2836 0.3411
7.750 1.0011 0.01553 0.00835 -0.0152 0.2823 0.3511
8.000 1.0214 0.01576 0.00864 -0.0143 0.2797 0.3666
8.250 1.0408 0.01603 0.00896 -0.0134 0.2773 0.3829
8.500 1.0596 0.01634 0.00933 -0.0125 0.2734 0.4178
9.000 1.3066 0.01674 0.01114 -0.0563 0.2641 0.9990
9.250 1.3401 0.01719 0.01159 -0.0585 0.2603 1.0000
9.500 1.3527 0.01771 0.01207 -0.0565 0.2533 1.0000
9.750 1.3694 0.01807 0.01245 -0.0551 0.2502 1.0000
10.000 1.3827 0.01859 0.01295 -0.0532 0.2434 1.0000
10.250 1.3959 0.01915 0.01348 -0.0514 0.2381 1.0000
10.500 1.4115 0.01959 0.01395 -0.0500 0.2339 1.0000
10.750 1.4253 0.02015 0.01451 -0.0484 0.2293 1.0000
11.000 1.4373 0.02082 0.01516 -0.0466 0.2237 1.0000
11.250 1.4470 0.02163 0.01592 -0.0445 0.2119 1.0000
11.500 1.4597 0.02230 0.01661 -0.0430 0.2081 1.0000
11.750 1.4666 0.02333 0.01757 -0.0407 0.1956 1.0000
12.000 1.4687 0.02467 0.01882 -0.0381 0.1786 1.0000
12.250 1.4702 0.02611 0.02019 -0.0355 0.1636 1.0000
12.500 1.4704 0.02770 0.02172 -0.0329 0.1490 1.0000
12.750 1.4680 0.02954 0.02349 -0.0303 0.1344 1.0000
13.000 1.4680 0.03131 0.02522 -0.0281 0.1238 1.0000
13.250 1.4678 0.03316 0.02705 -0.0260 0.1148 1.0000
13.500 1.4674 0.03512 0.02899 -0.0241 0.1068 1.0000
13.750 1.4696 0.03694 0.03082 -0.0226 0.1005 1.0000
14.000 1.4653 0.03935 0.03320 -0.0208 0.0916 1.0000
14.250 1.4594 0.04200 0.03584 -0.0191 0.0806 1.0000
14.500 1.4288 0.04705 0.04079 -0.0164 0.0558 1.0000
14.750 1.4016 0.05212 0.04586 -0.0145 0.0391 1.0000
15.000 1.3745 0.05750 0.05126 -0.0131 0.0221 1.0000
15.250 1.3599 0.06178 0.05559 -0.0125 0.0163 1.0000
15.500 1.3527 0.06532 0.05921 -0.0121 0.0144 1.0000
15.750 1.3485 0.06862 0.06259 -0.0119 0.0137 1.0000
16.000 1.3428 0.07216 0.06621 -0.0119 0.0130 1.0000
16.250 1.3348 0.07606 0.07019 -0.0120 0.0122 1.0000
16.500 1.3280 0.07985 0.07406 -0.0121 0.0115 1.0000
16.750 1.3215 0.08365 0.07794 -0.0124 0.0112 1.0000
17.000 1.3151 0.08749 0.08186 -0.0128 0.0110 1.0000
17.250 1.3070 0.09160 0.08605 -0.0133 0.0105 1.0000
17.500 1.2978 0.09586 0.09039 -0.0138 0.0100 1.0000
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Polar data table (+)
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