Glenn Martin 4 (glennmartin4-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: Glenn Martin 4 (glennmartin4-il) Reynolds number: 1,000,000 Max Cl/Cd: 77.51 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-glennmartin4-il-1000000-n5.txt Download as CSV file: xf-glennmartin4-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: Glenn Martin 4
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
------ -------- --------- --------- -------- -------- --------
-13.500 -0.7991 0.03672 0.03376 -0.1195 0.9519 0.0068
-13.250 -0.8147 0.03491 0.03184 -0.1130 0.9459 0.0068
-13.000 -0.8126 0.03216 0.02885 -0.1107 0.9439 0.0069
-12.750 -0.8010 0.03029 0.02682 -0.1093 0.9429 0.0069
-12.500 -0.7972 0.02898 0.02538 -0.1055 0.9394 0.0070
-12.250 -0.7971 0.02753 0.02377 -0.1010 0.9358 0.0071
-12.000 -0.7798 0.02636 0.02248 -0.0996 0.9340 0.0072
-11.750 -0.7624 0.02504 0.02102 -0.0982 0.9327 0.0072
-11.500 -0.7444 0.02368 0.01951 -0.0970 0.9318 0.0076
-11.250 -0.7455 0.02309 0.01885 -0.0913 0.9257 0.0076
-11.000 -0.7262 0.02222 0.01790 -0.0898 0.9232 0.0079
-10.750 -0.7061 0.02132 0.01689 -0.0885 0.9217 0.0079
-10.500 -0.6831 0.02053 0.01601 -0.0877 0.9206 0.0082
-10.250 -0.6710 0.01998 0.01539 -0.0844 0.9162 0.0085
-10.000 -0.6564 0.01930 0.01461 -0.0817 0.9117 0.0085
-9.750 -0.6333 0.01882 0.01406 -0.0808 0.9097 0.0088
-9.500 -0.6092 0.01817 0.01333 -0.0799 0.9080 0.0091
-9.250 -0.5837 0.01759 0.01266 -0.0794 0.9066 0.0095
-9.000 -0.5773 0.01720 0.01221 -0.0748 0.8982 0.0097
-8.750 -0.5558 0.01666 0.01162 -0.0734 0.8948 0.0101
-8.250 -0.5148 0.01580 0.01067 -0.0700 0.8824 0.0112
-8.000 -0.4872 0.01520 0.00999 -0.0698 0.8781 0.0114
-7.750 -0.4602 0.01477 0.00951 -0.0695 0.8726 0.0120
-7.500 -0.4210 0.01406 0.00869 -0.0717 0.8618 0.0124
-7.250 -0.3842 0.01352 0.00811 -0.0735 0.8546 0.0134
-7.000 -0.3277 0.01278 0.00724 -0.0795 0.8330 0.0143
-6.750 -0.2859 0.01239 0.00667 -0.0824 0.8039 0.0152
-6.500 -0.2647 0.01228 0.00638 -0.0808 0.7720 0.0158
-6.250 -0.2541 0.01228 0.00619 -0.0770 0.7290 0.0166
-6.000 -0.2521 0.01252 0.00615 -0.0713 0.6638 0.0172
-5.750 -0.2401 0.01264 0.00610 -0.0678 0.6235 0.0180
-5.500 -0.2224 0.01266 0.00600 -0.0655 0.6001 0.0190
-5.250 -0.2036 0.01256 0.00578 -0.0635 0.5837 0.0192
-5.000 -0.1833 0.01253 0.00568 -0.0618 0.5702 0.0203
-4.750 -0.1636 0.01244 0.00552 -0.0600 0.5585 0.0209
-4.500 -0.1429 0.01239 0.00544 -0.0585 0.5471 0.0219
-4.250 -0.1217 0.01233 0.00532 -0.0570 0.5384 0.0226
-4.000 -0.1009 0.01231 0.00523 -0.0554 0.5271 0.0236
-3.750 -0.0788 0.01222 0.00508 -0.0541 0.5196 0.0240
-3.500 -0.0566 0.01219 0.00499 -0.0529 0.5125 0.0247
-3.250 -0.0346 0.01205 0.00481 -0.0516 0.5057 0.0255
-3.000 -0.0125 0.01198 0.00468 -0.0503 0.4959 0.0260
-2.750 0.0104 0.01190 0.00456 -0.0493 0.4892 0.0274
-2.500 0.0339 0.01183 0.00445 -0.0484 0.4826 0.0282
-2.250 0.0571 0.01180 0.00437 -0.0474 0.4756 0.0291
-2.000 0.0813 0.01176 0.00429 -0.0466 0.4688 0.0300
-1.750 0.1051 0.01175 0.00423 -0.0458 0.4608 0.0307
-1.500 0.1296 0.01171 0.00415 -0.0451 0.4532 0.0323
-1.250 0.1540 0.01170 0.00410 -0.0445 0.4452 0.0337
-1.000 0.1787 0.01170 0.00406 -0.0439 0.4365 0.0349
-0.750 0.2031 0.01172 0.00404 -0.0433 0.4257 0.0371
-0.500 0.2284 0.01174 0.00403 -0.0429 0.4155 0.0409
-0.250 0.2535 0.01178 0.00410 -0.0425 0.4034 0.0602
0.000 0.2774 0.01188 0.00414 -0.0419 0.3915 0.0643
0.250 0.3013 0.01198 0.00420 -0.0413 0.3782 0.0692
0.500 0.3261 0.01206 0.00423 -0.0408 0.3692 0.0708
0.750 0.3500 0.01218 0.00429 -0.0402 0.3604 0.0733
1.000 0.3747 0.01228 0.00434 -0.0398 0.3510 0.0737
1.250 0.4007 0.01235 0.00438 -0.0397 0.3451 0.0759
1.500 0.4267 0.01242 0.00444 -0.0396 0.3399 0.0768
1.750 0.4531 0.01250 0.00450 -0.0396 0.3338 0.0794
2.000 0.4787 0.01260 0.00457 -0.0395 0.3291 0.0797
2.250 0.5058 0.01268 0.00464 -0.0397 0.3254 0.0810
2.500 0.5340 0.01276 0.00471 -0.0401 0.3210 0.0838
3.000 0.5885 0.01299 0.00491 -0.0408 0.3123 0.0905
3.250 0.6219 0.01299 0.00505 -0.0425 0.3096 0.1394
3.500 0.6513 0.01304 0.00517 -0.0434 0.3072 0.1750
4.000 0.8709 0.01275 0.00688 -0.0828 0.2955 0.9875
4.250 0.9149 0.01314 0.00726 -0.0870 0.2936 0.9932
4.500 0.9699 0.01349 0.00758 -0.0937 0.2910 0.9985
4.750 0.9976 0.01366 0.00774 -0.0943 0.2888 0.9992
5.000 1.0290 0.01384 0.00790 -0.0957 0.2859 1.0000
5.250 1.0491 0.01404 0.00808 -0.0945 0.2825 1.0000
5.500 1.0692 0.01423 0.00826 -0.0934 0.2804 1.0000
5.750 1.0896 0.01440 0.00843 -0.0923 0.2789 1.0000
6.000 1.1101 0.01457 0.00861 -0.0913 0.2774 1.0000
6.250 1.1303 0.01475 0.00882 -0.0902 0.2764 1.0000
6.500 1.1505 0.01494 0.00901 -0.0891 0.2727 1.0000
6.750 1.1706 0.01514 0.00922 -0.0881 0.2717 1.0000
7.000 1.1901 0.01537 0.00945 -0.0870 0.2691 1.0000
7.250 1.2086 0.01565 0.00970 -0.0857 0.2634 1.0000
7.500 1.2286 0.01585 0.00993 -0.0847 0.2605 1.0000
7.750 1.2472 0.01611 0.01019 -0.0834 0.2562 1.0000
8.000 1.2649 0.01642 0.01048 -0.0821 0.2517 1.0000
8.250 1.2830 0.01672 0.01079 -0.0808 0.2481 1.0000
8.500 1.3009 0.01703 0.01107 -0.0796 0.2396 1.0000
8.750 1.3174 0.01740 0.01143 -0.0781 0.2337 1.0000
9.000 1.3339 0.01776 0.01179 -0.0766 0.2260 1.0000
9.250 1.3483 0.01824 0.01223 -0.0748 0.2168 1.0000
9.500 1.3588 0.01891 0.01279 -0.0724 0.1988 1.0000
9.750 1.3680 0.01964 0.01345 -0.0699 0.1838 1.0000
10.000 1.3674 0.02087 0.01452 -0.0658 0.1565 1.0000
10.250 1.3669 0.02213 0.01566 -0.0619 0.1342 1.0000
10.750 1.3484 0.02578 0.01900 -0.0521 0.0719 1.0000
11.000 1.3382 0.02783 0.02100 -0.0475 0.0441 1.0000
11.250 1.3319 0.02976 0.02288 -0.0437 0.0220 1.0000
11.500 1.3356 0.03114 0.02426 -0.0414 0.0165 1.0000
11.750 1.3413 0.03244 0.02560 -0.0395 0.0144 1.0000
12.000 1.3478 0.03373 0.02694 -0.0378 0.0132 1.0000
12.250 1.3536 0.03512 0.02839 -0.0361 0.0124 1.0000
12.500 1.3570 0.03673 0.03005 -0.0344 0.0111 1.0000
12.750 1.3611 0.03835 0.03173 -0.0329 0.0109 1.0000
13.000 1.3640 0.04013 0.03357 -0.0315 0.0099 1.0000
13.250 1.3674 0.04193 0.03544 -0.0302 0.0098 1.0000
13.500 1.3686 0.04400 0.03758 -0.0290 0.0093 1.0000
13.750 1.3692 0.04623 0.03988 -0.0279 0.0091 1.0000
14.000 1.3690 0.04859 0.04231 -0.0270 0.0085 1.0000
14.250 1.3666 0.05126 0.04506 -0.0262 0.0081 1.0000
14.500 1.3642 0.05401 0.04788 -0.0256 0.0076 1.0000
14.750 1.3592 0.05714 0.05111 -0.0250 0.0074 1.0000
15.000 1.3557 0.06016 0.05421 -0.0246 0.0072 1.0000
15.250 1.3504 0.06343 0.05757 -0.0243 0.0071 1.0000
15.500 1.3450 0.06672 0.06095 -0.0242 0.0068 1.0000
15.750 1.3350 0.07063 0.06495 -0.0241 0.0066 1.0000
16.000 1.3287 0.07414 0.06853 -0.0241 0.0063 1.0000
16.250 1.3157 0.07852 0.07300 -0.0241 0.0058 1.0000
16.500 1.3076 0.08235 0.07695 -0.0243 0.0062 1.0000
16.750 1.2944 0.08689 0.08158 -0.0247 0.0059 1.0000
17.000 1.2850 0.09099 0.08579 -0.0251 0.0062 1.0000
17.250 1.2707 0.09580 0.09068 -0.0257 0.0057 1.0000
17.500 1.2574 0.10060 0.09558 -0.0264 0.0057 1.0000
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Polar data table (+)
Polar graphs
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