GOE 280 (DAIMLER XI) AIRFOIL (goe280-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 280 (DAIMLER XI) AIRFOIL (goe280-il) Reynolds number: 100,000 Max Cl/Cd: 56.76 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe280-il-100000-n5.txt Download as CSV file: xf-goe280-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 280 (DAIMLER XI) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3361 0.11302 0.10836 -0.0268 1.0000 0.0272
-8.250 -0.3350 0.11039 0.10580 -0.0277 1.0000 0.0272
-8.000 -0.3321 0.10755 0.10301 -0.0290 1.0000 0.0273
-7.750 -0.3286 0.10465 0.10017 -0.0304 1.0000 0.0273
-7.500 -0.3252 0.10175 0.09732 -0.0317 1.0000 0.0273
-7.250 -0.3214 0.09882 0.09444 -0.0328 1.0000 0.0273
-7.000 -0.3173 0.09587 0.09152 -0.0337 1.0000 0.0273
-6.750 -0.3126 0.09288 0.08856 -0.0345 1.0000 0.0274
-6.500 -0.3071 0.08984 0.08552 -0.0352 1.0000 0.0274
-6.250 -0.3029 0.08604 0.08178 -0.0353 1.0000 0.0275
-6.000 -0.3042 0.08139 0.07721 -0.0329 1.0000 0.0279
-5.750 -0.3022 0.07794 0.07379 -0.0312 1.0000 0.0284
-5.500 -0.2945 0.07455 0.07042 -0.0311 0.9991 0.0290
-5.250 -0.2641 0.06999 0.06580 -0.0364 0.9933 0.0314
-5.000 -0.2231 0.06524 0.06092 -0.0449 0.9870 0.0352
-4.750 -0.1607 0.06157 0.05680 -0.0574 0.9797 0.0385
-4.500 -0.1187 0.05752 0.05243 -0.0634 0.9741 0.0388
-4.250 -0.0924 0.05108 0.04600 -0.0672 0.9687 0.0398
-4.000 -0.0656 0.04717 0.04210 -0.0701 0.9638 0.0437
-3.750 -0.0177 0.04394 0.03836 -0.0759 0.9572 0.0534
-3.500 0.0157 0.04003 0.03443 -0.0795 0.9530 0.0577
-3.000 0.0908 0.03439 0.02824 -0.0862 0.9399 0.0866
-2.500 0.1751 0.02815 0.02093 -0.0901 0.9261 0.0562
-2.250 0.2129 0.02626 0.01842 -0.0910 0.9172 0.0535
-2.000 0.2510 0.02494 0.01669 -0.0923 0.9101 0.0519
-1.750 0.2814 0.02288 0.01448 -0.0931 0.8987 0.0551
-1.500 0.3129 0.02171 0.01311 -0.0936 0.8872 0.0567
-1.250 0.3448 0.02067 0.01174 -0.0937 0.8752 0.0550
-1.000 0.3752 0.01981 0.01067 -0.0936 0.8619 0.0541
-0.750 0.4044 0.01903 0.00976 -0.0934 0.8471 0.0538
-0.500 0.4331 0.01829 0.00893 -0.0931 0.8312 0.0540
-0.250 0.4615 0.01760 0.00817 -0.0928 0.8145 0.0546
0.000 0.4896 0.01697 0.00751 -0.0924 0.7971 0.0556
0.250 0.5169 0.01652 0.00702 -0.0918 0.7778 0.0590
0.500 0.5445 0.01621 0.00659 -0.0913 0.7581 0.0641
0.750 0.5721 0.01595 0.00616 -0.0908 0.7381 0.0651
1.000 0.5993 0.01582 0.00585 -0.0903 0.7161 0.0657
1.250 0.6267 0.01577 0.00559 -0.0898 0.6943 0.0665
1.500 0.6537 0.01575 0.00544 -0.0893 0.6706 0.0683
1.750 0.6804 0.01579 0.00533 -0.0889 0.6462 0.0714
2.000 0.7068 0.01586 0.00527 -0.0883 0.6200 0.0774
2.250 0.7277 0.01443 0.00539 -0.0871 0.5936 0.7414
2.500 0.7522 0.01429 0.00523 -0.0859 0.5645 1.0000
2.750 0.7776 0.01460 0.00528 -0.0852 0.5370 1.0000
3.000 0.8032 0.01493 0.00539 -0.0848 0.5132 1.0000
3.250 0.8291 0.01525 0.00556 -0.0844 0.4932 1.0000
3.500 0.8548 0.01558 0.00579 -0.0840 0.4741 1.0000
3.750 0.8805 0.01590 0.00604 -0.0837 0.4542 1.0000
4.000 0.9060 0.01623 0.00630 -0.0834 0.4343 1.0000
4.250 0.9312 0.01658 0.00658 -0.0830 0.4145 1.0000
4.500 0.9564 0.01693 0.00692 -0.0826 0.3941 1.0000
4.750 0.9812 0.01732 0.00726 -0.0822 0.3735 1.0000
5.000 1.0058 0.01772 0.00763 -0.0818 0.3524 1.0000
5.250 1.0300 0.01816 0.00807 -0.0813 0.3312 1.0000
5.500 1.0533 0.01867 0.00850 -0.0807 0.3056 1.0000
5.750 1.0743 0.01939 0.00896 -0.0799 0.2652 1.0000
6.000 1.0943 0.02026 0.00949 -0.0791 0.2214 1.0000
6.250 1.1153 0.02105 0.01010 -0.0784 0.1897 1.0000
6.500 1.1364 0.02183 0.01070 -0.0778 0.1630 1.0000
6.750 1.1568 0.02268 0.01137 -0.0770 0.1382 1.0000
7.000 1.1779 0.02344 0.01206 -0.0762 0.1210 1.0000
7.250 1.1979 0.02431 0.01284 -0.0753 0.0976 1.0000
7.750 1.2283 0.02710 0.01533 -0.0722 0.0220 1.0000
8.000 1.2448 0.02832 0.01668 -0.0707 0.0194 1.0000
8.250 1.2612 0.02948 0.01806 -0.0691 0.0175 1.0000
8.500 1.2775 0.03061 0.01942 -0.0676 0.0166 1.0000
8.750 1.2924 0.03183 0.02088 -0.0659 0.0161 1.0000
9.000 1.3052 0.03321 0.02251 -0.0640 0.0156 1.0000
9.250 1.3154 0.03472 0.02427 -0.0618 0.0153 1.0000
9.500 1.3233 0.03627 0.02613 -0.0594 0.0150 1.0000
9.750 1.3265 0.03793 0.02803 -0.0565 0.0145 1.0000
10.000 1.3275 0.03986 0.03020 -0.0537 0.0140 1.0000
10.250 1.3265 0.04204 0.03262 -0.0512 0.0137 1.0000
10.500 1.3234 0.04452 0.03533 -0.0490 0.0134 1.0000
10.750 1.3186 0.04732 0.03836 -0.0473 0.0133 1.0000
11.000 1.3124 0.05050 0.04176 -0.0461 0.0132 1.0000
11.250 1.3048 0.05412 0.04559 -0.0455 0.0132 1.0000
11.500 1.2960 0.05821 0.04989 -0.0456 0.0131 1.0000
11.750 1.2864 0.06273 0.05461 -0.0463 0.0131 1.0000
12.000 1.2761 0.06766 0.05974 -0.0475 0.0130 1.0000
12.250 1.2654 0.07291 0.06517 -0.0491 0.0130 1.0000
12.500 1.2547 0.07837 0.07081 -0.0510 0.0130 1.0000
12.750 1.2444 0.08389 0.07649 -0.0529 0.0130 1.0000
13.000 1.2349 0.08931 0.08206 -0.0548 0.0130 1.0000
13.250 1.2270 0.09446 0.08734 -0.0564 0.0130 1.0000
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Polar data table (+)
Polar graphs
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