GOE 223 (MVA H.34) AIRFOIL (goe223-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 223 (MVA H.34) AIRFOIL (goe223-il) Reynolds number: 1,000,000 Max Cl/Cd: 108.48 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe223-il-1000000.txt Download as CSV file: xf-goe223-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 223 (MVA H.34) 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
------ -------- --------- --------- -------- -------- --------
-15.500 -0.5806 0.07567 0.07328 -0.0924 0.9580 0.0162
-15.250 -0.6014 0.06910 0.06656 -0.0963 0.9487 0.0163
-15.000 -0.6136 0.06427 0.06159 -0.0990 0.9393 0.0164
-14.750 -0.6220 0.05981 0.05701 -0.1019 0.9294 0.0165
-14.500 -0.6281 0.05593 0.05301 -0.1044 0.9193 0.0167
-14.250 -0.6338 0.05237 0.04931 -0.1066 0.9082 0.0168
-14.000 -0.6369 0.04900 0.04581 -0.1090 0.8962 0.0170
-13.750 -0.6392 0.04577 0.04243 -0.1113 0.8847 0.0172
-13.500 -0.6403 0.04267 0.03917 -0.1135 0.8738 0.0174
-13.250 -0.6391 0.03976 0.03609 -0.1157 0.8635 0.0177
-13.000 -0.6358 0.03702 0.03319 -0.1180 0.8549 0.0180
-12.750 -0.6293 0.03457 0.03057 -0.1203 0.8467 0.0183
-12.500 -0.6194 0.03241 0.02826 -0.1229 0.8395 0.0185
-12.250 -0.5503 0.01733 0.01324 -0.1203 0.8233 0.0191
-12.000 -0.5398 0.01593 0.01179 -0.1220 0.8179 0.0193
-11.750 -0.5282 0.01471 0.01049 -0.1238 0.8126 0.0195
-11.500 -0.5155 0.01370 0.00942 -0.1260 0.8077 0.0198
-11.250 -0.4960 0.01272 0.00837 -0.1292 0.8032 0.0201
-11.000 -0.4740 0.01197 0.00753 -0.1319 0.7985 0.0204
-10.750 -0.4526 0.01121 0.00665 -0.1333 0.7938 0.0208
-10.500 -0.4302 0.01042 0.00577 -0.1344 0.7900 0.0213
-10.250 -0.4070 0.00972 0.00497 -0.1355 0.7860 0.0218
-10.000 -0.3827 0.00916 0.00429 -0.1364 0.7819 0.0222
-9.750 -0.3570 0.00892 0.00390 -0.1375 0.7777 0.0225
-9.500 -0.3494 0.01875 0.01349 -0.1419 0.7798 0.0231
-9.250 -0.3230 0.01813 0.01284 -0.1425 0.7755 0.0236
-9.000 -0.2954 0.01759 0.01229 -0.1432 0.7714 0.0241
-8.750 -0.2680 0.01706 0.01174 -0.1438 0.7670 0.0245
-8.500 -0.2405 0.01654 0.01117 -0.1443 0.7627 0.0250
-8.250 -0.2127 0.01604 0.01061 -0.1448 0.7584 0.0255
-8.000 -0.1844 0.01555 0.01009 -0.1453 0.7541 0.0260
-7.750 -0.1556 0.01521 0.00969 -0.1459 0.7492 0.0266
-7.500 -0.1264 0.01503 0.00941 -0.1465 0.7443 0.0269
-7.250 -0.1002 0.01398 0.00836 -0.1469 0.7394 0.0276
-7.000 -0.0723 0.01330 0.00768 -0.1476 0.7334 0.0281
-6.750 -0.0439 0.01285 0.00719 -0.1482 0.7272 0.0286
-6.500 -0.0146 0.01244 0.00676 -0.1489 0.7209 0.0292
-6.250 0.0145 0.01210 0.00638 -0.1495 0.7135 0.0299
-6.000 0.0437 0.01176 0.00600 -0.1501 0.7060 0.0305
-5.750 0.0729 0.01145 0.00561 -0.1506 0.6958 0.0309
-5.500 0.1021 0.01117 0.00527 -0.1512 0.6834 0.0314
-5.250 0.1310 0.01095 0.00497 -0.1516 0.6684 0.0318
-5.000 0.1597 0.01081 0.00472 -0.1519 0.6501 0.0321
-4.750 0.1880 0.01046 0.00421 -0.1524 0.6277 0.0330
-4.500 0.2158 0.01030 0.00390 -0.1527 0.6000 0.0340
-4.250 0.2435 0.01026 0.00370 -0.1529 0.5757 0.0348
-4.000 0.2715 0.01022 0.00355 -0.1532 0.5577 0.0355
-3.750 0.2999 0.01018 0.00341 -0.1534 0.5446 0.0363
-3.500 0.3285 0.01015 0.00329 -0.1537 0.5343 0.0372
-3.250 0.3573 0.01011 0.00319 -0.1540 0.5258 0.0380
-3.000 0.3863 0.01005 0.00307 -0.1543 0.5191 0.0400
-2.750 0.4150 0.01001 0.00298 -0.1546 0.5131 0.0433
-2.500 0.4449 0.00971 0.00283 -0.1553 0.5089 0.0942
-2.250 0.4751 0.00872 0.00247 -0.1569 0.5046 0.3014
-2.000 0.5040 0.00869 0.00251 -0.1573 0.5004 0.3389
-1.750 0.5327 0.00876 0.00257 -0.1575 0.4962 0.3548
-1.500 0.5622 0.00878 0.00259 -0.1578 0.4933 0.3647
-1.250 0.5913 0.00883 0.00264 -0.1581 0.4894 0.3746
-1.000 0.6201 0.00890 0.00269 -0.1584 0.4856 0.3820
-0.750 0.6485 0.00899 0.00276 -0.1586 0.4818 0.3885
-0.500 0.6773 0.00907 0.00282 -0.1588 0.4785 0.3930
-0.250 0.7065 0.00910 0.00285 -0.1591 0.4755 0.3977
0.000 0.7354 0.00915 0.00291 -0.1594 0.4720 0.4037
0.250 0.7639 0.00923 0.00297 -0.1596 0.4684 0.4083
0.500 0.7919 0.00936 0.00305 -0.1597 0.4646 0.4121
0.750 0.8205 0.00939 0.00310 -0.1600 0.4615 0.4173
1.000 0.8494 0.00943 0.00316 -0.1603 0.4583 0.4212
1.250 0.8778 0.00950 0.00322 -0.1605 0.4540 0.4251
1.500 0.9056 0.00961 0.00329 -0.1606 0.4497 0.4281
1.750 0.9333 0.00971 0.00337 -0.1607 0.4457 0.4307
2.000 0.9619 0.00973 0.00342 -0.1610 0.4421 0.4346
2.250 0.9899 0.00980 0.00350 -0.1611 0.4373 0.4380
2.500 1.0167 0.00994 0.00360 -0.1611 0.4307 0.4413
2.750 1.0446 0.01002 0.00368 -0.1612 0.4252 0.4446
3.000 1.0716 0.01015 0.00378 -0.1612 0.4181 0.4475
3.250 1.0983 0.01026 0.00389 -0.1612 0.4104 0.4521
3.500 1.1243 0.01042 0.00403 -0.1611 0.4002 0.4561
3.750 1.1499 0.01060 0.00417 -0.1608 0.3886 0.4600
4.000 1.1736 0.01088 0.00437 -0.1603 0.3714 0.4636
4.250 1.1937 0.01134 0.00467 -0.1592 0.3428 0.4678
4.500 1.1943 0.01281 0.00565 -0.1549 0.2579 0.4717
4.750 1.2064 0.01343 0.00614 -0.1524 0.2336 0.4762
5.000 1.2248 0.01385 0.00652 -0.1510 0.2227 0.4808
5.250 1.2445 0.01427 0.00691 -0.1499 0.2141 0.4858
5.500 1.2659 0.01460 0.00725 -0.1491 0.2087 0.4916
5.750 1.2857 0.01501 0.00765 -0.1481 0.2026 0.4974
6.000 1.3064 0.01538 0.00802 -0.1472 0.1973 0.5035
6.250 1.3264 0.01578 0.00843 -0.1463 0.1910 0.5107
6.500 1.3441 0.01631 0.00893 -0.1450 0.1815 0.5179
6.750 1.3559 0.01716 0.00968 -0.1430 0.1569 0.5263
7.000 1.3561 0.01871 0.01101 -0.1396 0.1185 0.5338
7.250 1.3718 0.01940 0.01174 -0.1383 0.1153 0.5441
7.500 1.3867 0.02016 0.01252 -0.1369 0.1116 0.5549
7.750 1.4029 0.02086 0.01327 -0.1358 0.1090 0.5680
8.000 1.4196 0.02154 0.01402 -0.1347 0.1075 0.5828
8.250 1.4371 0.02219 0.01475 -0.1338 0.1070 0.5990
8.500 1.4537 0.02291 0.01554 -0.1329 0.1062 0.6162
8.750 1.4696 0.02369 0.01640 -0.1319 0.1053 0.6336
9.000 1.4844 0.02456 0.01734 -0.1308 0.1042 0.6508
9.250 1.4981 0.02552 0.01838 -0.1297 0.1028 0.6672
9.500 1.5110 0.02656 0.01947 -0.1285 0.1015 0.6834
9.750 1.5225 0.02772 0.02071 -0.1273 0.0998 0.6999
10.000 1.5332 0.02897 0.02203 -0.1260 0.0977 0.7189
10.250 1.5432 0.03029 0.02348 -0.1248 0.0956 0.7478
10.500 1.5559 0.03079 0.02442 -0.1234 0.0947 1.0000
10.750 1.5717 0.03170 0.02535 -0.1227 0.0932 1.0000
11.000 1.5839 0.03292 0.02659 -0.1218 0.0899 1.0000
11.250 1.5900 0.03468 0.02833 -0.1204 0.0846 1.0000
11.500 1.5983 0.03630 0.02989 -0.1193 0.0726 1.0000
11.750 1.5683 0.04144 0.03484 -0.1159 0.0345 1.0000
12.000 1.5543 0.04539 0.03878 -0.1138 0.0185 1.0000
12.250 1.5558 0.04792 0.04136 -0.1127 0.0163 1.0000
12.500 1.5569 0.05056 0.04405 -0.1117 0.0151 1.0000
12.750 1.5586 0.05321 0.04676 -0.1108 0.0142 1.0000
13.000 1.5618 0.05573 0.04934 -0.1101 0.0138 1.0000
13.250 1.5641 0.05839 0.05207 -0.1095 0.0133 1.0000
13.500 1.5651 0.06122 0.05496 -0.1088 0.0129 1.0000
13.750 1.5647 0.06426 0.05807 -0.1082 0.0125 1.0000
14.000 1.5628 0.06752 0.06140 -0.1077 0.0121 1.0000
14.250 1.5585 0.07113 0.06509 -0.1072 0.0117 1.0000
14.500 1.5591 0.07414 0.06818 -0.1069 0.0115 1.0000
14.750 1.5597 0.07716 0.07126 -0.1066 0.0113 1.0000
15.000 1.5594 0.08032 0.07449 -0.1063 0.0111 1.0000
15.250 1.5582 0.08363 0.07787 -0.1061 0.0108 1.0000
15.500 1.5574 0.08687 0.08118 -0.1060 0.0105 1.0000
15.750 1.5553 0.09032 0.08469 -0.1059 0.0103 1.0000
16.000 1.5529 0.09378 0.08823 -0.1059 0.0101 1.0000
16.250 1.5494 0.09744 0.09195 -0.1059 0.0099 1.0000
16.500 1.5431 0.10154 0.09613 -0.1061 0.0097 1.0000
16.750 1.5354 0.10585 0.10053 -0.1064 0.0095 1.0000
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Polar data table (+)
Polar graphs
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