GOE 474 AIRFOIL (goe474-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: GOE 474 AIRFOIL (goe474-il) Reynolds number: 200,000 Max Cl/Cd: 70.06 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe474-il-200000-n5.txt Download as CSV file: xf-goe474-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 474 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4418 0.08672 0.08316 -0.0290 1.0000 0.0143
-8.500 -0.4466 0.08283 0.07934 -0.0301 1.0000 0.0143
-8.250 -0.4544 0.07911 0.07568 -0.0308 1.0000 0.0142
-8.000 -0.4660 0.07542 0.07208 -0.0314 1.0000 0.0140
-7.750 -0.4739 0.07071 0.06743 -0.0338 1.0000 0.0138
-7.500 -0.4802 0.06588 0.06264 -0.0360 1.0000 0.0139
-7.250 -0.4894 0.05959 0.05634 -0.0386 1.0000 0.0137
-7.000 -0.5060 0.03393 0.02971 -0.0530 0.9944 0.0131
-6.750 -0.4802 0.02917 0.02437 -0.0561 0.9890 0.0138
-6.500 -0.4512 0.02659 0.02135 -0.0580 0.9849 0.0152
-6.250 -0.4237 0.02381 0.01803 -0.0592 0.9798 0.0165
-6.000 -0.3931 0.02142 0.01512 -0.0604 0.9765 0.0176
-5.750 -0.3655 0.01989 0.01322 -0.0607 0.9710 0.0185
-5.500 -0.3356 0.01830 0.01147 -0.0617 0.9672 0.0211
-5.250 -0.3045 0.01735 0.01031 -0.0626 0.9635 0.0239
-5.000 -0.2755 0.01637 0.00911 -0.0629 0.9583 0.0264
-4.500 -0.2100 0.01461 0.00707 -0.0652 0.9520 0.0348
-4.250 -0.1823 0.01410 0.00640 -0.0651 0.9455 0.0392
-4.000 -0.1509 0.01342 0.00567 -0.0659 0.9414 0.0458
-3.750 -0.1173 0.01290 0.00512 -0.0671 0.9382 0.0548
-3.500 -0.0894 0.01250 0.00477 -0.0671 0.9315 0.0691
-3.250 -0.0572 0.01228 0.00459 -0.0680 0.9268 0.0963
-3.000 -0.0240 0.01217 0.00442 -0.0690 0.9229 0.1135
-2.750 0.0044 0.01206 0.00426 -0.0690 0.9161 0.1229
-2.500 0.0367 0.01194 0.00403 -0.0698 0.9114 0.1310
-2.250 0.0660 0.01179 0.00389 -0.0701 0.9051 0.1394
-2.000 0.0958 0.01166 0.00370 -0.0704 0.8990 0.1457
-1.750 0.1266 0.01146 0.00351 -0.0709 0.8942 0.1520
-1.500 0.1537 0.01139 0.00340 -0.0707 0.8866 0.1608
-1.250 0.1837 0.01120 0.00325 -0.0710 0.8813 0.1700
-1.000 0.2103 0.01108 0.00315 -0.0707 0.8735 0.1780
-0.750 0.2391 0.01094 0.00303 -0.0708 0.8678 0.1875
-0.500 0.2657 0.01082 0.00295 -0.0704 0.8599 0.1981
-0.250 0.2938 0.01066 0.00283 -0.0703 0.8512 0.2131
0.000 0.3200 0.01050 0.00274 -0.0697 0.8400 0.2371
0.250 0.3449 0.01023 0.00270 -0.0691 0.8291 0.3016
0.750 0.4489 0.00847 0.00268 -0.0788 0.8089 1.0000
1.000 0.4726 0.00851 0.00263 -0.0776 0.7917 1.0000
1.250 0.4962 0.00856 0.00259 -0.0764 0.7726 1.0000
1.500 0.5202 0.00862 0.00258 -0.0753 0.7547 1.0000
1.750 0.5444 0.00870 0.00259 -0.0743 0.7384 1.0000
2.000 0.5683 0.00879 0.00262 -0.0732 0.7198 1.0000
2.250 0.5914 0.00890 0.00263 -0.0719 0.6937 1.0000
2.500 0.6141 0.00905 0.00267 -0.0706 0.6635 1.0000
2.750 0.6368 0.00922 0.00274 -0.0693 0.6323 1.0000
3.000 0.6592 0.00943 0.00284 -0.0680 0.5990 1.0000
3.250 0.6803 0.00971 0.00296 -0.0664 0.5500 1.0000
3.500 0.6975 0.01022 0.00311 -0.0642 0.4679 1.0000
3.750 0.7143 0.01087 0.00339 -0.0620 0.4015 1.0000
4.000 0.7333 0.01142 0.00372 -0.0604 0.3505 1.0000
4.250 0.7530 0.01196 0.00407 -0.0589 0.3035 1.0000
4.500 0.7735 0.01247 0.00441 -0.0576 0.2625 1.0000
4.750 0.7942 0.01297 0.00478 -0.0563 0.2282 1.0000
5.000 0.8155 0.01345 0.00516 -0.0552 0.2017 1.0000
5.250 0.8370 0.01392 0.00559 -0.0541 0.1825 1.0000
5.500 0.8586 0.01439 0.00602 -0.0530 0.1655 1.0000
5.750 0.8801 0.01487 0.00647 -0.0519 0.1491 1.0000
6.000 0.9019 0.01533 0.00692 -0.0509 0.1357 1.0000
6.250 0.9236 0.01580 0.00743 -0.0498 0.1261 1.0000
6.500 0.9451 0.01627 0.00790 -0.0488 0.1143 1.0000
6.750 0.9670 0.01672 0.00834 -0.0479 0.0989 1.0000
7.000 0.9883 0.01723 0.00884 -0.0469 0.0858 1.0000
7.250 1.0095 0.01776 0.00938 -0.0459 0.0726 1.0000
7.500 1.0305 0.01832 0.00995 -0.0448 0.0543 1.0000
7.750 1.0486 0.01924 0.01075 -0.0434 0.0351 1.0000
8.000 1.0663 0.02023 0.01175 -0.0418 0.0259 1.0000
8.250 1.0831 0.02132 0.01287 -0.0401 0.0208 1.0000
8.500 1.1013 0.02219 0.01389 -0.0386 0.0182 1.0000
8.750 1.1181 0.02319 0.01503 -0.0370 0.0165 1.0000
9.000 1.1331 0.02433 0.01630 -0.0351 0.0151 1.0000
9.250 1.1435 0.02592 0.01802 -0.0327 0.0137 1.0000
9.500 1.1566 0.02718 0.01943 -0.0307 0.0127 1.0000
9.750 1.1696 0.02843 0.02085 -0.0287 0.0119 1.0000
10.000 1.1799 0.02982 0.02246 -0.0263 0.0115 1.0000
10.250 1.1882 0.03135 0.02415 -0.0238 0.0109 1.0000
10.500 1.1957 0.03290 0.02587 -0.0212 0.0105 1.0000
10.750 1.2018 0.03457 0.02772 -0.0188 0.0102 1.0000
11.000 1.2062 0.03640 0.02972 -0.0163 0.0100 1.0000
11.250 1.2087 0.03837 0.03185 -0.0139 0.0097 1.0000
11.500 1.2087 0.04059 0.03425 -0.0117 0.0094 1.0000
11.750 1.2055 0.04320 0.03704 -0.0095 0.0092 1.0000
12.000 1.1968 0.04654 0.04058 -0.0076 0.0089 1.0000
12.250 1.1911 0.04955 0.04383 -0.0063 0.0088 1.0000
12.500 1.1846 0.05263 0.04717 -0.0055 0.0086 1.0000
12.750 1.1761 0.05618 0.05097 -0.0053 0.0084 1.0000
13.000 1.1627 0.06077 0.05578 -0.0057 0.0084 1.0000
13.250 1.1511 0.06533 0.06058 -0.0071 0.0082 1.0000
13.500 1.1352 0.07110 0.06655 -0.0095 0.0083 1.0000
13.750 1.1168 0.07795 0.07363 -0.0131 0.0082 1.0000
14.000 1.0983 0.08567 0.08154 -0.0178 0.0082 1.0000
14.250 1.0784 0.09456 0.09060 -0.0235 0.0084 1.0000
14.500 1.0580 0.10421 0.10039 -0.0296 0.0085 1.0000
14.750 1.0356 0.11458 0.11086 -0.0357 0.0088 1.0000
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Polar data table (+)
Polar graphs
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