GOE 358 AIRFOIL (goe358-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 358 AIRFOIL (goe358-il) Reynolds number: 1,000,000 Max Cl/Cd: 119.22 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe358-il-1000000.txt Download as CSV file: xf-goe358-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 358 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -0.7512 0.08063 0.07840 -0.0548 1.0000 0.0167
-13.750 -0.7917 0.07007 0.06772 -0.0620 1.0000 0.0167
-13.500 -0.8260 0.06136 0.05890 -0.0679 1.0000 0.0166
-13.250 -0.8650 0.05506 0.05255 -0.0696 1.0000 0.0165
-13.000 -0.9001 0.04867 0.04609 -0.0731 1.0000 0.0164
-12.750 -0.9185 0.04196 0.03925 -0.0797 1.0000 0.0165
-12.500 -0.9117 0.03551 0.03263 -0.0892 0.9998 0.0167
-12.250 -0.8751 0.02995 0.02684 -0.1015 0.9985 0.0171
-12.000 -0.8342 0.02431 0.02093 -0.1139 0.9974 0.0178
-11.750 -0.7954 0.02081 0.01726 -0.1215 0.9965 0.0186
-11.500 -0.7606 0.01939 0.01573 -0.1250 0.9956 0.0194
-11.250 -0.7266 0.01837 0.01461 -0.1275 0.9949 0.0202
-11.000 -0.6925 0.01759 0.01371 -0.1297 0.9942 0.0209
-10.750 -0.6583 0.01624 0.01228 -0.1326 0.9935 0.0222
-10.500 -0.6269 0.01560 0.01159 -0.1340 0.9920 0.0233
-10.250 -0.5949 0.01505 0.01096 -0.1353 0.9906 0.0243
-10.000 -0.5621 0.01437 0.01019 -0.1368 0.9893 0.0255
-9.750 -0.5288 0.01386 0.00968 -0.1384 0.9881 0.0270
-9.500 -0.4950 0.01357 0.00935 -0.1397 0.9870 0.0284
-9.250 -0.4609 0.01329 0.00900 -0.1411 0.9860 0.0296
-9.000 -0.4264 0.01281 0.00853 -0.1427 0.9852 0.0315
-8.750 -0.3915 0.01265 0.00835 -0.1442 0.9844 0.0329
-8.500 -0.3562 0.01246 0.00812 -0.1457 0.9838 0.0343
-8.250 -0.3205 0.01204 0.00765 -0.1475 0.9832 0.0358
-8.000 -0.2888 0.01187 0.00750 -0.1482 0.9807 0.0372
-7.750 -0.2555 0.01171 0.00734 -0.1492 0.9780 0.0385
-7.500 -0.2216 0.01152 0.00710 -0.1503 0.9754 0.0398
-7.250 -0.1875 0.01141 0.00696 -0.1514 0.9729 0.0408
-7.000 -0.1549 0.01076 0.00625 -0.1525 0.9698 0.0426
-6.750 -0.1278 0.01051 0.00599 -0.1522 0.9633 0.0437
-6.500 -0.0984 0.01030 0.00577 -0.1523 0.9580 0.0450
-6.250 -0.0707 0.01012 0.00556 -0.1520 0.9508 0.0463
-6.000 -0.0428 0.00992 0.00530 -0.1518 0.9431 0.0474
-5.750 -0.0152 0.00981 0.00515 -0.1514 0.9339 0.0482
-5.500 0.0129 0.00946 0.00473 -0.1513 0.9250 0.0492
-5.250 0.0414 0.00893 0.00415 -0.1514 0.9147 0.0511
-5.000 0.0697 0.00870 0.00389 -0.1513 0.9037 0.0524
-4.750 0.0981 0.00851 0.00363 -0.1512 0.8913 0.0536
-4.500 0.1264 0.00836 0.00341 -0.1511 0.8770 0.0549
-4.250 0.1547 0.00821 0.00318 -0.1509 0.8604 0.0559
-4.000 0.1830 0.00810 0.00297 -0.1508 0.8409 0.0568
-3.750 0.2111 0.00805 0.00281 -0.1505 0.8192 0.0575
-3.500 0.2394 0.00790 0.00252 -0.1504 0.7974 0.0589
-3.250 0.2679 0.00776 0.00226 -0.1504 0.7769 0.0609
-3.000 0.2963 0.00770 0.00210 -0.1503 0.7584 0.0627
-2.750 0.3248 0.00765 0.00197 -0.1502 0.7431 0.0644
-2.500 0.3534 0.00762 0.00186 -0.1502 0.7298 0.0662
-2.000 0.4109 0.00753 0.00165 -0.1501 0.7056 0.0721
-1.750 0.4397 0.00746 0.00156 -0.1501 0.6941 0.0795
-1.500 0.4689 0.00717 0.00144 -0.1504 0.6822 0.1493
-1.250 0.4978 0.00687 0.00138 -0.1507 0.6694 0.2375
-1.000 0.5264 0.00686 0.00140 -0.1507 0.6558 0.2708
-0.750 0.5546 0.00691 0.00143 -0.1506 0.6389 0.2902
-0.500 0.5825 0.00701 0.00146 -0.1504 0.6188 0.3013
-0.250 0.6104 0.00713 0.00149 -0.1501 0.5949 0.3087
0.000 0.6378 0.00727 0.00154 -0.1499 0.5692 0.3163
0.250 0.6653 0.00745 0.00160 -0.1496 0.5432 0.3234
0.500 0.6928 0.00761 0.00168 -0.1494 0.5205 0.3297
0.750 0.7204 0.00776 0.00175 -0.1492 0.5005 0.3353
1.000 0.7480 0.00792 0.00183 -0.1490 0.4803 0.3404
1.250 0.7755 0.00808 0.00193 -0.1487 0.4602 0.3471
1.500 0.8028 0.00826 0.00203 -0.1485 0.4413 0.3533
1.750 0.8303 0.00843 0.00212 -0.1483 0.4249 0.3574
2.000 0.8579 0.00856 0.00222 -0.1481 0.4106 0.3631
2.250 0.8855 0.00870 0.00234 -0.1479 0.3982 0.3691
2.500 0.9129 0.00887 0.00245 -0.1477 0.3862 0.3739
2.750 0.9401 0.00902 0.00257 -0.1474 0.3745 0.3788
3.000 0.9677 0.00913 0.00268 -0.1472 0.3654 0.3831
3.250 0.9950 0.00929 0.00280 -0.1470 0.3573 0.3873
3.500 1.0227 0.00940 0.00292 -0.1468 0.3513 0.3909
3.750 1.0498 0.00954 0.00305 -0.1466 0.3443 0.3964
4.000 1.0774 0.00964 0.00318 -0.1464 0.3392 0.4016
4.250 1.1047 0.00977 0.00331 -0.1462 0.3340 0.4062
4.750 1.1591 0.01002 0.00361 -0.1457 0.3219 0.4171
5.000 1.1861 0.01016 0.00376 -0.1454 0.3163 0.4225
5.250 1.2129 0.01031 0.00392 -0.1451 0.3085 0.4285
5.500 1.2395 0.01048 0.00408 -0.1448 0.2984 0.4352
5.750 1.2662 0.01063 0.00425 -0.1445 0.2893 0.4421
6.000 1.2923 0.01084 0.00445 -0.1442 0.2771 0.4499
6.250 1.3180 0.01108 0.00465 -0.1437 0.2581 0.4575
6.500 1.3370 0.01204 0.00520 -0.1423 0.1839 0.4656
6.750 1.3589 0.01268 0.00571 -0.1413 0.1575 0.4746
7.000 1.3826 0.01309 0.00609 -0.1406 0.1433 0.4857
7.250 1.4060 0.01353 0.00649 -0.1398 0.1253 0.4998
7.750 1.4467 0.01495 0.00766 -0.1375 0.0678 0.5523
8.000 1.4656 0.01481 0.00819 -0.1359 0.0599 1.0000
8.250 1.4888 0.01521 0.00858 -0.1350 0.0558 1.0000
8.500 1.5103 0.01574 0.00909 -0.1340 0.0502 1.0000
8.750 1.5334 0.01609 0.00946 -0.1331 0.0470 1.0000
9.000 1.5540 0.01665 0.00998 -0.1319 0.0417 1.0000
9.250 1.5758 0.01706 0.01040 -0.1309 0.0380 1.0000
9.500 1.5958 0.01761 0.01093 -0.1296 0.0339 1.0000
9.750 1.6155 0.01814 0.01145 -0.1282 0.0307 1.0000
10.000 1.6340 0.01873 0.01205 -0.1267 0.0280 1.0000
10.250 1.6523 0.01929 0.01262 -0.1251 0.0260 1.0000
10.500 1.6668 0.02006 0.01339 -0.1230 0.0238 1.0000
10.750 1.6833 0.02057 0.01395 -0.1211 0.0228 1.0000
11.000 1.6964 0.02119 0.01461 -0.1186 0.0217 1.0000
11.250 1.7074 0.02196 0.01541 -0.1160 0.0207 1.0000
11.500 1.7149 0.02297 0.01647 -0.1129 0.0195 1.0000
11.750 1.7276 0.02369 0.01726 -0.1107 0.0190 1.0000
12.000 1.7388 0.02454 0.01816 -0.1084 0.0183 1.0000
12.250 1.7489 0.02548 0.01916 -0.1061 0.0177 1.0000
12.500 1.7569 0.02661 0.02033 -0.1037 0.0170 1.0000
12.750 1.7601 0.02815 0.02193 -0.1009 0.0163 1.0000
13.000 1.7651 0.02962 0.02350 -0.0985 0.0158 1.0000
13.250 1.7735 0.03091 0.02486 -0.0966 0.0155 1.0000
13.500 1.7799 0.03242 0.02645 -0.0948 0.0151 1.0000
13.750 1.7852 0.03410 0.02820 -0.0930 0.0147 1.0000
14.000 1.7897 0.03595 0.03012 -0.0915 0.0143 1.0000
14.250 1.7921 0.03809 0.03233 -0.0900 0.0140 1.0000
14.500 1.7923 0.04057 0.03490 -0.0887 0.0137 1.0000
14.750 1.7885 0.04364 0.03805 -0.0876 0.0133 1.0000
15.000 1.7786 0.04752 0.04206 -0.0867 0.0130 1.0000
15.250 1.7730 0.05109 0.04574 -0.0861 0.0128 1.0000
15.500 1.7717 0.05424 0.04900 -0.0857 0.0127 1.0000
15.750 1.7690 0.05764 0.05250 -0.0856 0.0125 1.0000
16.000 1.7650 0.06132 0.05628 -0.0856 0.0123 1.0000
16.250 1.7594 0.06532 0.06039 -0.0858 0.0122 1.0000
16.500 1.7527 0.06958 0.06476 -0.0862 0.0120 1.0000
16.750 1.7452 0.07401 0.06930 -0.0868 0.0118 1.0000
17.000 1.7371 0.07861 0.07400 -0.0876 0.0116 1.0000
17.250 1.7279 0.08349 0.07897 -0.0885 0.0115 1.0000
17.500 1.7187 0.08842 0.08400 -0.0896 0.0113 1.0000
17.750 1.7082 0.09356 0.08924 -0.0908 0.0112 1.0000
18.000 1.6971 0.09887 0.09466 -0.0922 0.0111 1.0000
18.250 1.6855 0.10436 0.10024 -0.0938 0.0109 1.0000
18.500 1.6731 0.10998 0.10596 -0.0955 0.0108 1.0000
18.750 1.6600 0.11575 0.11182 -0.0974 0.0107 1.0000
19.000 1.6470 0.12160 0.11776 -0.0995 0.0106 1.0000
19.250 1.6326 0.12772 0.12398 -0.1018 0.0104 1.0000
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