CURTISS CR-1 AIRFOIL (cr1-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: CURTISS CR-1 AIRFOIL (cr1-il) Reynolds number: 100,000 Max Cl/Cd: 54.68 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-cr1-il-100000.txt Download as CSV file: xf-cr1-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: CURTISS CR-1 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3549 0.11265 0.10821 -0.0223 1.0000 0.1239
-8.250 -0.3834 0.11259 0.10824 -0.0266 0.9964 0.1266
-8.000 -0.4042 0.11037 0.10608 -0.0353 0.9869 0.1274
-7.750 -0.3440 0.10324 0.09885 -0.0305 0.9888 0.1303
-7.500 -0.3236 0.09989 0.09547 -0.0330 0.9845 0.1339
-7.250 -0.3182 0.09713 0.09271 -0.0364 0.9781 0.1383
-7.000 -0.3592 0.09577 0.09131 -0.0506 0.9621 0.1424
-6.750 -0.3330 0.09089 0.08651 -0.0461 0.9610 0.1440
-6.500 -0.3057 0.08796 0.08355 -0.0447 0.9582 0.1476
-6.250 -0.2953 0.08519 0.08076 -0.0473 0.9522 0.1528
-6.000 -0.3040 0.08107 0.07651 -0.0576 0.9415 0.1589
-5.750 -0.2835 0.07797 0.07345 -0.0556 0.9383 0.1608
-5.500 -0.2786 0.07602 0.07151 -0.0535 0.9315 0.1634
-5.250 -0.2640 0.07212 0.06731 -0.0638 0.9246 0.1747
-5.000 -0.2602 0.06981 0.06509 -0.0598 0.9185 0.1762
-4.750 -0.2446 0.06772 0.06303 -0.0583 0.9133 0.1802
-4.500 -0.2191 0.06399 0.05901 -0.0651 0.9083 0.1922
-4.250 -0.2248 0.04997 0.04394 -0.0694 0.9006 0.1285
-4.000 -0.2033 0.04635 0.03997 -0.0701 0.8956 0.1255
-3.750 -0.1738 0.04211 0.03509 -0.0720 0.8919 0.1262
-3.500 -0.1676 0.03991 0.03241 -0.0690 0.8847 0.1271
-3.250 -0.1423 0.03831 0.03078 -0.0693 0.8793 0.1300
-3.000 -0.1041 0.03741 0.02975 -0.0713 0.8754 0.1368
-2.750 -0.0955 0.03618 0.02800 -0.0682 0.8672 0.1416
-2.500 -0.0645 0.03528 0.02710 -0.0690 0.8617 0.1477
-2.250 -0.0214 0.03415 0.02555 -0.0714 0.8580 0.1593
-2.000 -0.0161 0.03428 0.02578 -0.0679 0.8481 0.1643
-1.750 0.0233 0.03350 0.02473 -0.0697 0.8432 0.1766
-1.500 0.0394 0.03353 0.02477 -0.0679 0.8346 0.1842
-1.250 0.0735 0.03296 0.02405 -0.0688 0.8284 0.1955
-1.000 0.1078 0.03262 0.02349 -0.0696 0.8224 0.2072
-0.750 0.1283 0.03237 0.02331 -0.0684 0.8134 0.2153
-0.500 0.1761 0.03154 0.02239 -0.0713 0.8094 0.2290
-0.250 0.1875 0.03172 0.02251 -0.0686 0.7983 0.2371
0.000 0.2348 0.03086 0.02165 -0.0713 0.7939 0.2519
0.250 0.2501 0.03093 0.02173 -0.0692 0.7831 0.2620
0.500 0.2973 0.03001 0.02086 -0.0718 0.7784 0.2806
0.750 0.3517 0.02890 0.01982 -0.0754 0.7752 0.3084
1.000 0.3646 0.02897 0.02000 -0.0729 0.7630 0.3255
1.250 0.4309 0.02747 0.01878 -0.0786 0.7608 0.3763
1.500 0.5990 0.02402 0.01690 -0.1040 0.7616 1.0000
1.750 0.6170 0.02418 0.01694 -0.1017 0.7500 1.0000
2.000 0.6666 0.02322 0.01582 -0.1041 0.7449 1.0000
2.250 0.6871 0.02322 0.01574 -0.1021 0.7331 1.0000
2.500 0.7373 0.02211 0.01450 -0.1045 0.7273 1.0000
2.750 0.7568 0.02208 0.01442 -0.1023 0.7143 1.0000
3.000 0.7861 0.02170 0.01398 -0.1015 0.7034 1.0000
3.250 0.8259 0.02096 0.01313 -0.1024 0.6943 1.0000
3.500 0.8463 0.02089 0.01304 -0.1004 0.6806 1.0000
3.750 0.8708 0.02070 0.01280 -0.0990 0.6675 1.0000
4.000 0.8994 0.02036 0.01240 -0.0982 0.6550 1.0000
4.250 0.9306 0.01993 0.01190 -0.0979 0.6423 1.0000
4.500 0.9558 0.01968 0.01159 -0.0966 0.6274 1.0000
4.750 0.9784 0.01951 0.01137 -0.0949 0.6110 1.0000
5.000 0.9968 0.01948 0.01132 -0.0926 0.5926 1.0000
5.250 1.0164 0.01946 0.01123 -0.0905 0.5732 1.0000
5.500 1.0378 0.01945 0.01113 -0.0887 0.5533 1.0000
5.750 1.0604 0.01952 0.01106 -0.0873 0.5334 1.0000
6.000 1.0805 0.01976 0.01116 -0.0854 0.5125 1.0000
6.250 1.0983 0.02014 0.01143 -0.0833 0.4911 1.0000
6.500 1.1175 0.02057 0.01170 -0.0815 0.4710 1.0000
6.750 1.1375 0.02109 0.01205 -0.0799 0.4520 1.0000
7.000 1.1578 0.02168 0.01246 -0.0785 0.4342 1.0000
7.250 1.1764 0.02233 0.01300 -0.0768 0.4176 1.0000
7.500 1.1952 0.02301 0.01362 -0.0752 0.4027 1.0000
7.750 1.2128 0.02373 0.01432 -0.0735 0.3892 1.0000
8.000 1.2319 0.02450 0.01507 -0.0721 0.3772 1.0000
8.250 1.2557 0.02528 0.01575 -0.0715 0.3668 1.0000
8.500 1.2744 0.02603 0.01654 -0.0700 0.3568 1.0000
8.750 1.2941 0.02687 0.01739 -0.0688 0.3480 1.0000
9.000 1.3164 0.02765 0.01814 -0.0680 0.3396 1.0000
9.250 1.3359 0.02858 0.01914 -0.0669 0.3325 1.0000
9.500 1.3545 0.02941 0.02006 -0.0655 0.3255 1.0000
9.750 1.3796 0.03032 0.02094 -0.0653 0.3188 1.0000
10.000 1.3893 0.03118 0.02198 -0.0625 0.3120 1.0000
10.250 1.4203 0.03196 0.02262 -0.0633 0.3049 1.0000
10.500 1.4248 0.03295 0.02390 -0.0598 0.2993 1.0000
10.750 1.4409 0.03387 0.02492 -0.0582 0.2937 1.0000
11.000 1.4715 0.03484 0.02582 -0.0589 0.2880 1.0000
11.250 1.4717 0.03592 0.02720 -0.0549 0.2830 1.0000
11.500 1.4862 0.03664 0.02799 -0.0531 0.2766 1.0000
11.750 1.5008 0.03747 0.02885 -0.0514 0.2699 1.0000
12.000 1.4997 0.03830 0.02986 -0.0472 0.2637 1.0000
12.250 1.5202 0.03865 0.03009 -0.0463 0.2555 1.0000
12.500 1.5089 0.03969 0.03139 -0.0408 0.2507 1.0000
12.750 1.5272 0.03990 0.03150 -0.0396 0.2429 1.0000
13.000 1.5218 0.04109 0.03290 -0.0355 0.2380 1.0000
13.250 1.5154 0.04219 0.03418 -0.0315 0.2326 1.0000
13.500 1.5341 0.04241 0.03427 -0.0305 0.2250 1.0000
13.750 1.5189 0.04411 0.03628 -0.0261 0.2208 1.0000
14.000 1.5191 0.04502 0.03726 -0.0235 0.2146 1.0000
14.250 1.5240 0.04595 0.03824 -0.0215 0.2087 1.0000
14.500 1.5096 0.04800 0.04056 -0.0183 0.2039 1.0000
14.750 1.5214 0.04816 0.04058 -0.0169 0.1960 1.0000
15.000 1.5003 0.05095 0.04371 -0.0140 0.1917 1.0000
15.250 1.4899 0.05299 0.04589 -0.0120 0.1854 1.0000
15.500 1.4824 0.05490 0.04786 -0.0105 0.1786 1.0000
15.750 1.4646 0.05814 0.05135 -0.0091 0.1726 1.0000
16.000 1.4556 0.06056 0.05379 -0.0082 0.1650 1.0000
16.250 1.4342 0.06496 0.05848 -0.0079 0.1583 1.0000
16.500 1.4183 0.06894 0.06254 -0.0080 0.1500 1.0000
16.750 1.3955 0.07440 0.06821 -0.0090 0.1415 1.0000
17.000 1.3717 0.08056 0.07456 -0.0105 0.1322 1.0000
17.250 1.3484 0.08707 0.08117 -0.0126 0.1227 1.0000
17.500 1.3217 0.09449 0.08865 -0.0153 0.1126 1.0000
17.750 1.2951 0.10228 0.09652 -0.0183 0.1040 1.0000
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