HQ 2.1/9.5 AIRFOIL (hq2195-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 2.1/9.5 AIRFOIL (hq2195-il) Reynolds number: 500,000 Max Cl/Cd: 79.05 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq2195-il-500000-n5.txt Download as CSV file: xf-hq2195-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.1/9.5 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5079 0.09122 0.08882 -0.0299 1.0000 0.0100
-10.250 -0.5197 0.08433 0.08197 -0.0334 1.0000 0.0102
-9.500 -0.7369 0.02920 0.02548 -0.0586 0.9991 0.0107
-9.250 -0.7146 0.02553 0.02128 -0.0609 0.9933 0.0112
-9.000 -0.6871 0.02422 0.01984 -0.0623 0.9882 0.0115
-8.750 -0.6567 0.02340 0.01893 -0.0638 0.9843 0.0119
-8.500 -0.6281 0.02213 0.01747 -0.0651 0.9794 0.0123
-8.250 -0.5992 0.02072 0.01584 -0.0663 0.9742 0.0128
-8.000 -0.5687 0.01928 0.01414 -0.0678 0.9699 0.0133
-7.750 -0.5400 0.01816 0.01281 -0.0685 0.9633 0.0139
-7.500 -0.5089 0.01733 0.01180 -0.0697 0.9575 0.0145
-7.250 -0.4803 0.01610 0.01038 -0.0704 0.9501 0.0150
-7.000 -0.4512 0.01519 0.00937 -0.0711 0.9424 0.0155
-6.750 -0.4233 0.01455 0.00865 -0.0714 0.9337 0.0160
-6.500 -0.3951 0.01398 0.00799 -0.0717 0.9258 0.0165
-6.250 -0.3686 0.01347 0.00740 -0.0716 0.9165 0.0171
-6.000 -0.3418 0.01299 0.00683 -0.0715 0.9082 0.0179
-5.750 -0.3154 0.01252 0.00626 -0.0713 0.8994 0.0185
-5.500 -0.2892 0.01206 0.00571 -0.0710 0.8912 0.0189
-5.250 -0.2628 0.01166 0.00522 -0.0708 0.8831 0.0193
-5.000 -0.2371 0.01107 0.00456 -0.0705 0.8754 0.0201
-4.750 -0.2105 0.01070 0.00413 -0.0703 0.8683 0.0210
-4.500 -0.1836 0.01040 0.00380 -0.0702 0.8618 0.0220
-4.250 -0.1565 0.01016 0.00351 -0.0700 0.8552 0.0233
-4.000 -0.1292 0.00993 0.00320 -0.0699 0.8492 0.0246
-3.750 -0.1020 0.00966 0.00289 -0.0698 0.8426 0.0262
-3.500 -0.0746 0.00942 0.00263 -0.0697 0.8370 0.0292
-3.250 -0.0469 0.00924 0.00242 -0.0697 0.8316 0.0329
-3.000 -0.0194 0.00904 0.00223 -0.0696 0.8259 0.0413
-2.750 0.0080 0.00886 0.00206 -0.0695 0.8184 0.0548
-2.500 0.0349 0.00866 0.00190 -0.0693 0.8082 0.0772
-2.250 0.0620 0.00843 0.00176 -0.0692 0.7979 0.1128
-2.000 0.0888 0.00810 0.00161 -0.0691 0.7891 0.1769
-1.750 0.1143 0.00732 0.00142 -0.0692 0.7799 0.3632
-1.500 0.1404 0.00686 0.00137 -0.0691 0.7715 0.4988
-1.250 0.1675 0.00673 0.00134 -0.0689 0.7636 0.5472
-1.000 0.1948 0.00662 0.00135 -0.0687 0.7563 0.5935
-0.750 0.2220 0.00655 0.00139 -0.0685 0.7496 0.6388
-0.500 0.2494 0.00652 0.00142 -0.0682 0.7430 0.6751
-0.250 0.2770 0.00652 0.00143 -0.0680 0.7358 0.6927
0.000 0.3049 0.00652 0.00143 -0.0679 0.7286 0.7025
0.250 0.3327 0.00653 0.00143 -0.0678 0.7206 0.7112
0.500 0.3606 0.00655 0.00144 -0.0677 0.7121 0.7201
0.750 0.3881 0.00657 0.00146 -0.0675 0.7028 0.7282
1.000 0.4159 0.00659 0.00148 -0.0674 0.6916 0.7367
1.250 0.4433 0.00661 0.00151 -0.0672 0.6788 0.7456
1.500 0.4704 0.00666 0.00155 -0.0670 0.6621 0.7543
1.750 0.4972 0.00672 0.00158 -0.0666 0.6388 0.7638
2.000 0.5226 0.00687 0.00162 -0.0660 0.5970 0.7740
2.250 0.5451 0.00727 0.00172 -0.0649 0.5230 0.7849
2.500 0.5671 0.00780 0.00194 -0.0639 0.4482 0.7967
2.750 0.5906 0.00821 0.00214 -0.0632 0.3959 0.8098
3.000 0.6153 0.00847 0.00231 -0.0626 0.3634 0.8239
3.250 0.6405 0.00868 0.00248 -0.0621 0.3395 0.8388
3.750 0.6905 0.00901 0.00280 -0.0609 0.3036 0.8727
4.000 0.7149 0.00916 0.00296 -0.0602 0.2853 0.8939
4.250 0.7388 0.00936 0.00314 -0.0594 0.2582 0.9246
4.500 0.7707 0.00975 0.00336 -0.0606 0.2129 1.0000
4.750 0.7944 0.01028 0.00366 -0.0601 0.1673 1.0000
5.000 0.8177 0.01087 0.00401 -0.0595 0.1244 1.0000
5.250 0.8420 0.01133 0.00435 -0.0591 0.0995 1.0000
5.500 0.8669 0.01172 0.00467 -0.0587 0.0840 1.0000
5.750 0.8919 0.01209 0.00499 -0.0584 0.0726 1.0000
6.000 0.9169 0.01245 0.00533 -0.0580 0.0639 1.0000
6.250 0.9415 0.01284 0.00569 -0.0576 0.0556 1.0000
6.500 0.9664 0.01319 0.00604 -0.0572 0.0490 1.0000
6.750 0.9906 0.01360 0.00643 -0.0567 0.0413 1.0000
7.000 1.0144 0.01406 0.00686 -0.0561 0.0338 1.0000
7.250 1.0383 0.01450 0.00730 -0.0556 0.0295 1.0000
7.500 1.0615 0.01501 0.00780 -0.0550 0.0262 1.0000
7.750 1.0850 0.01545 0.00830 -0.0544 0.0246 1.0000
8.000 1.1080 0.01593 0.00882 -0.0537 0.0231 1.0000
8.250 1.1302 0.01649 0.00940 -0.0530 0.0215 1.0000
8.500 1.1511 0.01717 0.01014 -0.0520 0.0202 1.0000
8.750 1.1732 0.01768 0.01072 -0.0512 0.0195 1.0000
9.000 1.1947 0.01823 0.01134 -0.0504 0.0187 1.0000
9.250 1.2156 0.01881 0.01199 -0.0495 0.0178 1.0000
9.500 1.2357 0.01944 0.01267 -0.0485 0.0170 1.0000
9.750 1.2546 0.02015 0.01343 -0.0473 0.0162 1.0000
10.000 1.2700 0.02114 0.01448 -0.0457 0.0152 1.0000
10.250 1.2889 0.02176 0.01519 -0.0446 0.0148 1.0000
10.500 1.3062 0.02246 0.01600 -0.0432 0.0143 1.0000
10.750 1.3221 0.02320 0.01684 -0.0417 0.0137 1.0000
11.000 1.3360 0.02394 0.01765 -0.0398 0.0131 1.0000
11.250 1.3491 0.02468 0.01846 -0.0379 0.0125 1.0000
11.500 1.3604 0.02554 0.01938 -0.0359 0.0120 1.0000
11.750 1.3664 0.02679 0.02070 -0.0334 0.0114 1.0000
12.000 1.3766 0.02777 0.02180 -0.0315 0.0111 1.0000
12.250 1.3868 0.02879 0.02294 -0.0297 0.0108 1.0000
12.500 1.3950 0.02999 0.02425 -0.0279 0.0104 1.0000
12.750 1.4019 0.03134 0.02574 -0.0262 0.0100 1.0000
13.000 1.4087 0.03274 0.02725 -0.0246 0.0096 1.0000
13.250 1.4153 0.03421 0.02881 -0.0233 0.0093 1.0000
13.500 1.4214 0.03578 0.03048 -0.0221 0.0090 1.0000
13.750 1.4244 0.03770 0.03251 -0.0209 0.0088 1.0000
14.000 1.4249 0.03995 0.03486 -0.0200 0.0085 1.0000
14.250 1.4226 0.04264 0.03767 -0.0192 0.0083 1.0000
14.500 1.4236 0.04511 0.04029 -0.0188 0.0081 1.0000
14.750 1.4204 0.04819 0.04353 -0.0187 0.0079 1.0000
15.000 1.4175 0.05142 0.04691 -0.0189 0.0077 1.0000
15.250 1.4115 0.05522 0.05086 -0.0196 0.0076 1.0000
15.500 1.4050 0.05936 0.05516 -0.0208 0.0074 1.0000
15.750 1.3970 0.06404 0.05999 -0.0225 0.0072 1.0000
16.000 1.3860 0.06959 0.06570 -0.0251 0.0071 1.0000
16.250 1.3770 0.07520 0.07145 -0.0280 0.0070 1.0000
16.500 1.3588 0.08278 0.07922 -0.0321 0.0070 1.0000
16.750 1.3432 0.09022 0.08681 -0.0363 0.0069 1.0000
17.000 1.3245 0.09847 0.09523 -0.0410 0.0069 1.0000
17.250 1.3016 0.10779 0.10471 -0.0464 0.0069 1.0000
17.500 1.2780 0.11755 0.11463 -0.0521 0.0069 1.0000
17.750 1.2544 0.12762 0.12485 -0.0581 0.0069 1.0000
18.000 1.2271 0.13899 0.13639 -0.0649 0.0070 1.0000
18.250 1.1994 0.15102 0.14858 -0.0722 0.0071 1.0000
18.500 1.1659 0.16522 0.16294 -0.0809 0.0072 1.0000
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